Piper PA-28-181 Archer II Pilot Operating Handbook Download

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Summary of Contents for PA-28-181 Archer II

Page 1: ...20 FAAAPPROVED BY DATE OF APPROVAL JULY 2 1979 DUPLICAIE WARD EVANS D O A NO SO 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA FAA APPROVED I N NORMAL AND UTILITY CATEGORIES BASED ON CAR 3 THIS HANDB...

Page 2: ...AIRCRAFT THIS HAND BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED Published by...

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Page 5: ...the text of the present handbook and or to add information to cover added airplane equipment I Revisions Revisions will be distributed whenever necessary as complete page replacements or additions an...

Page 6: ...the physical location of material on a page will not be identified ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below Title ii through vii 1 1 through...

Page 7: ...Revised para 2 7 d 8 Revised para 2 9 a Added placards Revised wording Revised wording Corrected spelling Revised para 4 9 Revised wording Revised Table of Contents Revised Figure 6 5 Revised Figure 6...

Page 8: ...f om pg 6 32 added new items 265 ard26l Relocated item ti om pg 6 33 renurnbered items Relocated and renun rbered items from pg 6 34 added new item 285 Renumbered items added ncw items 289 291 295 Re...

Page 9: ...8 21 a b Added pg added new info Added pg relocated mate rial from pg 8 12 and 8 I3 added cautions and revised infb c Relocated inlb to pg 8 12 added info fiom pg 8 14 Relocated info to pg 8 13 added...

Page 10: ...New page relocated para 3 29 from pg 3 14 and para 3 31 from pg 3 15 New page added relocated info Added item 61 Added item204 Revised item267 Added item2 74 revised item 275 moved items 283 and 285...

Page 11: ...d items 435 thru 441 fiom pg 6 42 moved infb to pg 6 44 New page relocated infb from pg 6 43 Revised para 7 I3 Revised para 7 15 Revised figure 7 1 I Cont para 7 l5 revision Cont para 7 15 revision Re...

Page 12: ...cl item 281 from pg 6 33 Revised item 291 Revised items 421 429 and 43 moved itern 433 to pg 6 43 Relocaled revised item 433 trompg 6 42 Removed info Revised para 7 I 1 Revised para 7 15 Revised Iable...

Page 13: ...4 l8 added para 4 23 and para 4 25 fuompg 4 16 Relocated para 4 29 info to pg 4 19 relocated pan 4 3l to pg 4 19 andpg 4 24 added para 4 21 info from pg 4 17 Relocated info to pg 4 2A added para 4 29...

Page 14: ...dded item 307 from pg 6 36 Relocated item 325 to pg 6 39 added items 313 and 315 fiom pg 6 37 Relocated item 329 to pg 6 40 and renumbered itern relocated item 331 to pg 6 40 revised item 328 added ne...

Page 15: ...relocated infb from pg 3 i Expanded normal procedure index moved info to new pg 4 ii New pg relocated infb frorn pg 4 i Revised para 4 1 Revised index pg Revised fig 6 5 info Revised fig 6 7 info Adde...

Page 16: ...5 3 thru 5 7 7 12 1 13 t 9 t t2 2 t0 6 9 8 2 8 3 9 67 thru 9 70 8 2 8 3 Added new Suppiement 7 Added new Supplement 8 Deleted para l 2l and pages Revised para 5 5 Relocated info frorn pg 7 13 Moved i...

Page 17: ...ing Added info to para 4 27 Revised charts Revissd para 7 11 Relocated inlb from pg 7 10 Added infb to para 7 15 Added info to parc 7 25 Revised Table of Contents Added Supplement 10 Aux Vac System vl...

Page 18: ...vised fig 6 1 1 Revised para 6 9 Added fig 6 17 title Moved para 7 39 tt t pg 7 26 Revised para 7 37 Added Narco ELT 910 inforrnation Added page Relocated para 7 39 from pg 7 24 Revised para 7 39 Revi...

Page 19: ...120 vi k Revised Pages Description of Revisions 9 71 7 26 vi k vi l 9 i 7 i 7 26 7 _17 7 28 vi k z 1 3 6 1 9 1 10 9 15 Added log of revision page Added log of revision page Added Supplement l1 to T O...

Page 20: ...PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Number and Code REPORT Vts 1120 vi l Approval Signature and Date Revised Pages Description of Revisions...

Page 21: ...8 SECTION 9 sEcTtoN 10 TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HA...

Page 22: ...T HIS PAGE INTENTIONALLY LEFT BLANK REPORT VB l120 viii...

Page 23: ...Introduction Engines Propellers Fuel oil 1 1 1 3 1 5 1 7 r 9 1 11 1 13 1 15 t l7 1 l9 1 1 1 3 1 3 l 3 l 4 l 4 t 4 1 5 1 5 r 6 Maximum Weights Standard Airplane Weights Baggage Space Specific Loadings...

Page 24: ...Paragraph No REPORT VB 1120 l lt TABLE OF CONTENTS SECTION 1 cont THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 25: ...also responsible for remaining within the operating limitations as outlined by instrument tnarkings placards and this handbook Although the arrerngement of this handbook is intended to increase its in...

Page 26: ...RAL PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II I I t ta lt THREE VIEW Figure l 1 Wing Arcr sq fi Min Turning Radius fi from pivot point to wingtiP t70 0 30 0 ttf t ltr I t REPORT VB 1120 t 2 ISSUE...

Page 27: ...aximum Continuous Power BHP g Maximum Continuous Engine Speed RPM h Bore inches i Stroke inches 0 Displacernent cubic inches k Compression Ratio l Engine Type I Lycorning O 360 A4M or o 360 A4A 180 27...

Page 28: ...rnbient Temp for Starting 1 Above 60 F 2 30 F to 90 F 3 0 F to 70 F 4 Below 10 F l 11MAXIMUM WEIGHTS a Maximum Rarnp Weight lbs b Maximum Takeoff Weight lbs c Maximum Landing Weight lbs d Maximum Weig...

Page 29: ...SECTION 1 GENERAL 1 15 BAGGAGE SPACE a Compartment Volume cubic feet b Entry Width inches c Entry Height inches 1 17 SPECIFIC LOADINGS a Wing Loading lbs per sq ft b Power Loading lbs per hp 24 22 20...

Page 30: ...Speed is the speed of an airplane relative to the ground Indicated Airspeed is the speed of an air craft as shown on the airspeed indicator when corrected for instrument error IAS values published in...

Page 31: ...Climb Speecl is the airspeed I which delivers the greatest gain of altitude in the shortest possible horizontal distance Best Rate of Climb Speed is the airspeed I which delivers the greatest gain in...

Page 32: ...standard sea level pressure 29 92 in Hg by a pressure or barornetric altirneter It is the indicated pressure altitude corrected for position and instrument error In this handbook altimeter instlument...

Page 33: ...ance required to accelerate an air Distance plane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the airplane to a stop Route Segment A part of a...

Page 34: ...he airplane The arm obtained by adding the airplane s individual moments and dividing the sum by the total weight The extreme center of gravity locations within which the airplane must be operated at...

Page 35: ...ERAL Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight Maximum weight approved for the start of the takeofT run Maximum weight approved for the landing touchdown Maximum weight ex...

Page 36: ...SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB L120 1 12 ISSUED JULY 2 1979...

Page 37: ...1 2 19 2 21 2 23 2 25 Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings 2 1 2 1 _ 2 3 2 4 2 4 2 5 2 6 2 6 2 6 2 6 a1 2 8 Weight Limits Ccntcr of Cravity Lirnits Maneu...

Page 38: ...Paragraph No REPORT VB 1120 z tt TABLE OF CONTENTS SECTION2 LIMITATIONS THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 39: ...the operating lirnitations stated in the form of placards and markings and those given in this section and this complete handbook Limitations associated with those optional systems ancl equipment whi...

Page 40: ...G Red Radial Line Never Exceecl Yellow Arc Caution Range Smooth Air Only Green Arc Normal Operating Range White Arc Flap Down REPORT VB 1120 t KIAS KCAS 113 89 111 89 CAUTION Maneuvering speecl decrea...

Page 41: ...line 8 Fuel AVGAS ONLY minimum grade 9 Nurnber of Propellers 1 0 Propeller Manufacturer 11 Propeller Model 12 Propeller Diameter Minimum Maximum 13 Propeller Toierance static RPM at maximum permissibl...

Page 42: ...nd Warm Up Red Line Minimurn Red Line Maxirnum d Fuel Pressure Green Arc Normal Operating Range Red Line Minimum Red Line Maximum 500 to 2650 RPM 2650 to 2700 RPM 27OO RPM 75 to245 F 245 F 60 PSI to 9...

Page 43: ...ion between points given The datum used is 78 4 inches ahead of the wing leading eclge at the inboard intersection of the straight and taperecl section It is the responsibility of the airplane owtrer...

Page 44: ...ty b Unusable Fuel The unusable tuel fbr this airplane has been determined as 1 0 gallon in each wing in clitical l1ight attitudes c Usable Fuel The usable t uel in this airplane has been determined a...

Page 45: ...ptable or unacceptable for operation at into or out o1 any airport The above statement not withstanding the noise level stated above has been verified by and approved by the Federal Aviation Administr...

Page 46: ...ROBATIC MANEUVERS ARE APPROVED FOR NORMAL CATEGORY OPERATIONS SPINS ARE PROHIBITED FOR NORMAL AND UTILITY CATEGORY In full view of the pilot TAKEOFF CHECK LIST Fuel on proper tank Electric fuel pump o...

Page 47: ...FLIGHT On insicle 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 WE...

Page 48: ...RS ARE LIMTTED TO THEFOLLOWING 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 49: ...r caps FUEL 100 or 100LL AVIATION GRADE or FUEL IOO 130 AVIATION GRADE MIN USABLECAPACITY 24GAL USABLE CAPACITY TO BOTTOM OF FILLER NECKINDICAIOR 17 GAL Adjacent to the filler caps serial numbers 28 8...

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Page 51: ...ternator Switch Electrical Overload Separate Rattery and Alternator Switch Spin Recovery 3 5 3 7 3 9 3 1 1 3 13 3 r5 3 17 3 19 3 21 3 23 1 t 3 t 3 8 3 8 3 8 3 9 3 9 3 9 3 10 3 11 3 11 3 12 3 13 3 l3 3...

Page 52: ...LE OF CONTENTS cont SECTION 3 cont Paragraph No 3 24 Electrical Overload Page No 3 25 Spin Recovery J J J J J 14 l5 15 T6 L6 3 21 Open Door 3 29 Carburetor Icing 3 31 Engine Roughness REPORT VB 1120 t...

Page 53: ...f the section is devoted to amplified emergency pro cedures containing additional intormation to provide the pilot with a more complete understanding of the procedutes These procedures are suggestecl...

Page 54: ...SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORt VB 1120 a t ISSUED JALY 2 1979...

Page 55: ...WER LOSS DURING TAKEOFF If suflicient runway remains fbr a normal landing land straight aheacl If insufficient runway remains Maintain saf e airspeed Make only shallow turn to avoicl obstrltctions Fla...

Page 56: ...containing fuel When power is restored Carburetor heat Electric luel pump If power is not restored prepare for power off landing Trim for 76 KIAS POWER OFF LANDING Locate suitable field Establish spir...

Page 57: ...rrottle Mixture CLOSED Electric fuel purnp idle cut off check OFF Heater and defroster OFF Pr oceed with power off landing procedure LOSS OF OIL PRESSURE Land as soon as possible and investigate cause...

Page 58: ...verify inop alt Reduce electrical loads to minirnum T1lil Tffi T ALT switch ON If power not restored ALT switch OFF If alternator output cannot be restored reduce electrical loads and land as soon as...

Page 59: ...1981 Reduce to Minimum NOTE Due to 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...

Page 60: ...position If both latches are open latch side latch then top latch CARBURETOR ICING Carburetor heat ON Mixture adjust for maxirnurn smoothness ENGINE ROUGHNESS Carburetor heat ON If roughness continue...

Page 61: ...his is an attenlpt to draw the fire back into the engine If the engine has started coutinue operating to try to pull the fire into the engine In either case above if fire continues more than a I ew se...

Page 62: ...h 3 13 An airspeed of at least 76 KIAS should be main tained If altitudc permits switch the fuel selector to another tank containing luel and turn the electric fuel pump ON Move the mixtr rre control...

Page 63: ...spiral pattern around this fleld Try to be at 1000 feet above the field at the downwincl position to make a normal landing approach When the field can easily be reached slow to 66 KIAS with tlaps down...

Page 64: ...e either partial or complete A partial loss o1 oil pressure usually indicates a malfunction in the oii pressure regulating system and a landing should be made as soon as possible to investigate the ca...

Page 65: ...ELECTRICAL FAILURES Loss of alternator output is detected through zero reading on the ammeter Before executing the following procedure insur e that the reading is zero and not merely low by actuating...

Page 66: ...nd ALT switch operation when the electrical load cannot be re duced turn the ALT switch OFF and land as soon as practical The batrery is the only rernaining source of electrical power Also anticipate...

Page 67: ...quirecl to smoothly regain a level flight attitude 3 27 OPEN DOOR The cabin door is double latched so the chances of its spr inging open in flight at both the top and side are remote However should yo...

Page 68: ...s usually due to carburetor icing which is indicated by a drop in RPM and rnay be accompanied by a slight loss of airspeed or altitude lf too much ice is allowed to accumulate restoration of full powe...

Page 69: ...g 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 systeln When using carburetor heat therefore a...

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Page 71: ...fore Starting Engine Starting Engine When Cold Starting Engine When Hot Starting Engine When Flooded Starting With External Power Source Warm Up Taxiing Ground Check Before Takeoff Preflight Check War...

Page 72: ...graph No Page No 4 25 4 27 4 29 4 3t 4 33 4 35 4 31 4 39 4 4r Climb Cruising Descent Approach and Landing Stopping Engine 4 r 1 4 r7 4 18 4 t9 4 20 4 20 4 2r 4 21 Aaa A LL Stalls Tlrrbulent Air Operat...

Page 73: ...themselves with the procedures given in this section in order to become prolicient in the normal operations of the airplane The trrst portion of this section consists of a short form check list which...

Page 74: ...ndition of the engine airplane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed b Best Angle of Clirnb Speed c Turbulent Air Operating Speed See Subsection 2 3 d...

Page 75: ...Control wheel release belts Avionics Fuel quantity gauges check Master switch OFF Ignition oFF Exterior check lbr darnage Control surfaces check fbr interference Hinges fi ee ol iceo snow frost check...

Page 76: ...ose gear strut proper inflation 3 25 in Air inlets c1ear Alternator belt Tow bar and control locks Baggage stowed properly secure Baggage door close and secure Fuel strainer drain and check for water...

Page 77: ...rottle adjust check STARTING ENGINE WHEN FLOODED Throttle open full Master switch ON Oil pressure Mixture Starter Mixture Tlrrottle idle cut off Oil pressure check STARTING WITH EXTERNAL POWER SOURCE...

Page 78: ...rc Throttle BEFORE IAKEOF F Master switch Flight instrurnents Fuel selector Electric luel pump Carburetor heat Seat backs Mixture Primer IIEPORT VB 1120 4 6 removed clear apply slowly check check r d...

Page 79: ...de After breaking ground accelerate to 45 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 Accelera...

Page 80: ...ef erence perfbrmance charts and Avco Lycoming Operator s Manual Normal max power 157o Power set per power table Mixture adjust DESCENT NORMAL Throttle Airspeed Mixture Carburetor heat every 30 second...

Page 81: ...etract Air conditioner Trim ro 75 KIAS OFF Final approach speed f1aps 40 66 KIAS STOPPING ENGINE Flaps Magnetos OFF OFF Master switch PARKING Parking brake Control wheel set secured with belts Flaps h...

Page 82: ...ht on the step Upon entering the cockpit release the seat belts securing the control wheel Turn OFF all avionics equipment Turn ON the master switch and check the fuel quantity gauges for sufficient f...

Page 83: ...g thc cnginc Each quick drain should be checked after closing it to make sure it has closed completely and is not leaking Check all of the luel tank vents to make sure they are open Next complete a ch...

Page 84: ...ility to all controls including fuel selector tIaps trim etc while maintaining adequate restraint fbr the occupant If the inertia reel type shoulder harness is installed a pull test of its locking res...

Page 85: ...engine fires release the magneto switch advance the tnixture and retard the throttle d Starting Engine With External Power Source An optional feature called the Piper External liower PEP aliows the op...

Page 86: ...rnal power supply 4 15 WARM UP Warm up the engine at 800 to 1200 RPM br not morc than two minutcs in warm weather and four ninutes in cold Avoid prolonged idling at low RPM as this practice may result...

Page 87: ...ed 50 RPM Operation on one magneto should not exceed 10 seconds Check tlre vacuum gauge the indicator should read 5 0 1 Hg at 2000 RPM Check the annunciator panel lights with the press to test button...

Page 88: ...nd shoulder harness should be fastened and adjusted Fasten the seaf belts snugly around ths gmpty seats NOTE If the fixed shoulder harness non inertia reel type is installed it must be connected to th...

Page 89: ...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 clirnbing out 4 2s CLrMB I The best rate of clirn...

Page 90: ...EGT is reached If this occurs the EGT corresponding to the onset of engine roughness shouid be used as the peak ret erence value Always remember that the elcctric fuel purrp should be turned ON befor...

Page 91: ...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 If the inertia reel type shoulder...

Page 92: ...raft weight on the rnain wheeis 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 93: ...of altitude during stalls varies frorn 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...

Page 94: ...EIGHT AND BALANCE It is the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs csnter of gravity envelope while in flight For weight and balanc...

Page 95: ...S SECTION 5 PERFORMANCE Paragraph No Page No 5 1 5 3 5 5 5 7 5 l 5 l 5 3 5 9 5 9 General Introduction to Performance and Flight Planning Flight Planning Example Performance Graphs List of Figures REPO...

Page 96: ...Puagraph REPORT VB 1150 5 il TABLE OF CONTENTS SECTION 5 cont THIS PAGE INTENTIONALLY LEFT BLANK Page No No...

Page 97: ...for the various parameters of weight altitude temperature etc The perfbrmance charts are unfactored and do not make any allowance for varying degrees of pilot proliciency or mechanical deterioration o...

Page 98: ...outlines a detailed flight plan using the perfbrmance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapo lation beyond...

Page 99: ...ght of the airplane Make use of the Weight and Balance Loading Forrn Figure 6 I I and the C G Range and Weight graph Figure 6 15 to deter mine the total weight of the airpiane and the center of gravit...

Page 100: ...itions at the destination airport and when established the landing weight The conditions and calculations for the example flight are listed below The takeolT and landing distances required for the exa...

Page 101: ...b segment of the flight plan corrected for field pressure altitude and temperature The following values wet e determined from the above instruo tions in the flight planning exatnple l Cruise Plessure...

Page 102: ...tal cruise distance Refer to the appropriate Avco Lycorning Operator s Manual when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise p...

Page 103: ...the total fuel required by adding the fuel to climb the fuel to descend and the cruise fuel When the total fuel in gallons is determined multiply this value by 6 lb gal to determine the total fuel wei...

Page 104: ...SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28 1 81 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORn VB 1120 5 8 ISSUED JULY 2 1979...

Page 105: ...Distance and Fuel to Climb Engine Perfbrmance Speed Power Performance Cruise Speed Power Economy Cruise Best Power Mixture Range Best Economy Mixture Range Endurance Time Distance and Fuel to Descend...

Page 106: ...SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28 1 81 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1 120 5 10 ISSUED JALY 2 1979...

Page 107: ...ION PA 28 181 ARCHER II SECTION 5 PERFORMANCE 100 90 80 70 60 50 40 30 20 10 o 10 2A 30 40 10 2 40 40 30 20 10 FAHRENHEIT DEGREES TEMPERATURE CONVERSION Figure 5 1 cEtstus DEGREES REPORT VB 1120 5 11...

Page 108: ...c t 60 ao REPORT VB 1120 5 12 o o z I I o Ut ul L o E o ul G o txl 60 o m to 90 r00 tro lro tlo rao 16 r rco 1 o t lAs t o t sT8uitEt TCnRoR AIRSPEED SYSTENI CALIBRATION Figure 5 3 AIRSPEED SYSTEM CAT...

Page 109: ...oa OG 9o E IE U E 90 u 3d R o fr2 o rHal oE il o u F 9 o 2 i t 6 C 5 5 il 1 I G o 6 o a E o o E g a 6 HRt f 6 t at fl iE oo6 gFsE cr trdi 6 c J ll b e I I I I too ii l l li iil o c o U a o lrJ UI L Q...

Page 110: ...TAKEOFF PERFORMANCE Figure 5 7 o l t 5 a 0 o o o 2 t I o z t e o I I I u 3 t aa il t o 8 rl n t 5 a a o 0 o n o o t I 2 t E o rl 4 trt gt sl lrl G lt r G a I G o tl u rl F o G I t tt r_l c t AI 5 B ti...

Page 111: ...z t ah o J I I I U I d g 8 5 I n F o F I N I o 4 Att Jx a kxe ai E 9E E I 3ee 68 C t 6l 5 t a o 5 a a 3 a E o e i o I r a o 3 o 5 c E a U o d o 9r4 oI U oC U R9 o o3 TO G o o t a 0 o o a F FOaFa Sart...

Page 112: ...11 8t tna id 3p o oZ F I oCt 2 ol li I I a g ut F F I N I o o 6 o I 9o I Il ol g ci t ll o od 5 oo n a nE t gE g I g3E i 3 tsi fd3 d 3 it ia o t a a a f E g a a 5 5E o 3 ET lo u I a o a Ia F REPORT V...

Page 113: ...a I t C It l g F F I N I o 8 a il I 5 a o i I c r ol a T op c 9A lll oQ ct tr go t ls TE tggi 1gc 3 E E E l9 9srI g63f t Q I s 5 2 o o t a a o A t 6 A 3 5 5E EE E io u REPORT VB 1 120 5 17 I il il ll...

Page 114: ...n I J c rl I q 5 o o n t o t c g t TE EO ed Ect al a ao if a 1r te I I Ei i ooc I C aa o CLIMB PERFORMANCE Figure 5 15 REPORT VI 1120 5 1 8 tff tl 3 f E t h i o rl 2 rl l j I g a I o llil E Eg 9 i Lt...

Page 115: ...4 o e 3a c at ET c g 1c ao EFe E gfi E iY d tr IEE t c 9 EEg9 i tp f 5 i ao tstoo aaaa 89EE ooo tt lt o gl t o 2 x lll l tt at ul o 3 J c l I urO cin hl rg E o I lr6 oll ie D 6t E J 3 9 FF rl lll o 3...

Page 116: ...a T I ri oa d i t aa F t fr I 1 l I ut I ll o I o I I G tt 8 o at c t x E J ul 3 o t F o lrl a li I t I t a ft T t G I o u H l ul 2 ll F 6 r I o N I G I a I ur F E rt o I F D o a fi i 51 3lE s5P i g a...

Page 117: ...ORMANCE 8 6 to gE 3 x iit 3 O3 d c a 33 5 E iioo i E33ls tu Jo F u t F o F I o N I o 8 o E o F o z i I o Il t t t t 3 I E I o i t oH o el o 8 5 oO t SPEED POWER PERFORMANCE CRUISE Figure 5 21 ISSUED J...

Page 118: ...I 6 a o E o u o o F o u 2 llt o t o n o o F o 2 Y I o ur U A 0 ll u G F l F ry o d ct g I o lu lrl o o lil oii ca ig i r r r3o 3F F o ao 5lr E i loo ui o o o t o I a I u c u E a 5 o SPEED POWER ECONO...

Page 119: ...it ffi tiiiililliilffi f E o It I d I 6 o g g a r J c 5 2 I g C 2 c I A lrl c t I 6 f o N I q t J t a rl o 3 2 o a 3 o a t o C l l t t o a I I a 5 G o T J a a a 0 2 a G 2 L a 0a o a O c 3 c a O a c I...

Page 120: ...I t y tr o ga 9 E C o 0 It x t o 2 5 8 o 3 J a 3 a I g 3 g lt I a t t Il I o F o U 2 3 lriil tilll tlffi H t a t c g J i E a I u 0 2 G I a I Il ut o ai 5 o O 1 z REPORT VB 1120 5 24 a r ta c d o H T...

Page 121: ...I o 3 a t o t t rr tt 2 3 l o 2 LI tont ll ttntSrra a a C REPORT VB 1120 1 a 6 c f o I I ul x c t o 2 rl tl U o 5 5 ot 3 J a t a F a E d a a a a o c a o c a t E c UJ It ai o a t u b 6C F E It t r OC c...

Page 122: ...EE E i xgE ao E x I ooccY c 1 E P I8TE E uoootIi o o 2 u v gr o o u 3 lt o 2 8t C z F ul a l o t o o F o F I o N I o o I a E lt c ul o ah 3 o o o o l o o I TIME DIS TANCE AND UEL TO DESCENI Figure 5 3...

Page 123: ...lltl I I t I I I I il Ir fl li H flt il ilillt I I I It o a a G ai J t aA h 3t r9 lt at lt o G U o a lU 9 2 E ul o J o ilt iil Ir lil F 0 F I o I o i E a 9 a G o I I 3 g r t i a t c Et E rO ri 5 t c o...

Page 124: ...DING PERT ORMANCE Figure 5 35 8 o o 3 o o z I I o 5 g 9 naO Fi QI ilH t3 t 5 o o O o t F o F I N I o I d T gl c ql e th l t o o l o d o o o g fl ir E i rE gN 39 dlulE E 3 E 3ltoo g g 3S E REPORT VB 11...

Page 125: ...5 37 t I fl tt F o 2 I I o 2 t 5 o o at tn o t a g ll 3 o o I 9a t u oF G oi tul o oi qF t oo 6 o i P iE d i H 3 1u Xl E 9E ooJ l Sns Esr 5 F F I N I o 8 N t E t o 3 a o a 8 i t a E o UJ REPORT VB l1...

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Page 127: ...2 6 5 6 9 6 I2a 6 13 6 14 6 l5 6 17 6 19 6 20 6 21 e Instruments 1 Miscellaneous g Engine and Engine Accessories Optional Equipment h Propeller and Propeller Accessories Optional Equipment i Landing...

Page 128: ...Paragraph No REPORT VB 1120 6 ii TABLE OF CONTENTS SECTION 6 cont THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 129: ...rmance it will have Center of gravity is a cletermining factor in flight characteristics If the C G is too far iorward in any airplane it may be difficult to rotate for takeofT or landing If the C G i...

Page 130: ...Note that the useful load includes usable fuel baggage cargo and passengers Iiollowing this is the method lbr computing takeoff weight and C C 6 3 AIRPLANE WEIGHING PROCEDURE At the time of licensing...

Page 131: ...tracted 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 pr...

Page 132: ...d Basic Empty Weight Center of Gravity 1 The following geometry applies to the PA 28 l8l airplane when it is level Refer to Leveling paragraph 6 3 b G Arm Lcvel Points Fuselags E 4 Wing l eading Edge...

Page 133: ...e airplane as licensecl at the factory These figures I apply only to the specific airplane serial number and registration number shown The basic empty weight of the airplane as licensed at the fzrctor...

Page 134: ...Optional Equiprnent Basic Ernpty Weight xTlre standard empty weight includes full oil capacity and 2 0 galions of unusable fuei AIRPLANE USEFUL LOAD Ramp Weight Basic Empty Weight Useful Load Norrnal...

Page 135: ...STREET 990 Keystone Park Rd MODEL PA28 181 CITY Derry S N 28 8090186 STATE Pa ZIP 15627 3688 N 3562G WEIGHT 1611 03 ARM 87 79 MOMENT 1 41433 26 PREVIOUS Install ST 901 Remote Convertor ST 901 Remote...

Page 136: ...z a bo d a 8B lE oo E 1L E dqJ Ee o 3 3 E a 2 c o tt L 2 oo e l oo c C E U s p a c to co o Ec polouto1 pappv O o E t z a J9 9 E6 ll ELt 96 o a iu Ho u o il E a J J 6 ol t O oN uall qt t o WEIGHT AND B...

Page 137: ...ARCHER II J 3 E z o0 o HF CO q oo o 5E d trl o tra o o 5 t o E z o ll a0 c b0 c cl U o0 o c c O o ic psnouaX pappv o E z rt a 6 o LO 5 _ c b Yo o 2 LL go o o oO c l ei 0N uall o H WEIGHT AND tsALANCE...

Page 138: ...ht 1s90 0 87 5 139125 Pilot and Front Passenger 340 0 80 s 27370 Passengers Rear Seats 340 0 118 1 40r54 Fuel 48 Gallon Maximum 288 0 95 0 27360 Baggage 200 Lbs Maximum 142 8 Ramp Weight 2558 Lbs Norm...

Page 139: ...al 2130 Lbs Utility Maximum Totals must be within approved weight and C C lirnits It is the responsi bility of the airplane owner and the pilot to insure rhat the airylane is loaded properly The Basic...

Page 140: ...CORPORATION PA 28 181 ARCHER II SECTION 6 WEIGHT AND BALANCE agt a0 360 il 2tE0 2S t80 ro 60 lo 15202530t6 ffl cr n00 Foln D8 r cHE3l LOADING GRAPH Figure 6 13 ao a6 50 REPORT VB 1120 6 11 o z 7 7 ISS...

Page 141: ...ATION PA 28 18I ARCHER II I GAII t a n I t I t I I u tot t Yt G O Ervrrorc 2tto llt r x oioaSw iloirArcAl oorv a7 at c o toc nox oxcrc3 Afr oArurl to to t2 tt C G RANGE AND WEIGHT Figure 6 15 REPORT V...

Page 142: ...n 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 gricl to locate the basic weight and C C location This can be put o...

Page 143: ...velope 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 slotted plastic into position so that the dot is under...

Page 144: ...AR I 8Er rl i I I WEIGHI vs c G cr vEroPE 2560 t8S mAI GROSS WT I ORMAL CATCGORY SAMPLE PROBLEM e3 9i 92 93 87 86 86 83 v a ISSUED MAY 29 1980 REVISED FEBRUARY 2 1990 82 83 ttt7t0t9 c c tocalro lrrcfi...

Page 145: ...PIPER AIRCRAFT CORPORATION PA 28 1 81 ARCHER II SECTION 6 WEIGHTAND BALANCE THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1l20 6 tzd ISSUED JULY 2 L979...

Page 146: ...which were installed on the airplane described below when licensed by the manufacturer Where the letter A 8 or C precedes an item A denotes an item which is required equipment that must be installed...

Page 147: ...F E tal H z o a FI F gr F bJ o o a Propeller and Propeller Accessories ltem Item IA 3 A Propeller Sensenich 76EM8S5 62 Piper Spec PS50077 42 Cert Basis TC P4EA Spinner Piper Dwg 65805 0 a Bulkhead b D...

Page 148: ...Cert Basis TC E285 Oil Filter a Lycoming No 75528 AC OF5s78770 b Lycoming No LW 13743 Champion CH48ll0 Cert Basis TC E286 Alternator 60 Amp a Chrysler 4l I lEl0 b Prestolite ALY6 CI8 Engine Driven Fu...

Page 149: ...oducts lnc P N 65122 Oil Cooler Piper Dwg 18622 Harrison P N C 8526250 or Niagara P N N D M 20002A Mark if Instl Weight Pounds 0 4 1 9 0 9 t8 0 Moment Lb ln Arm ln Aft Datum 6 t 9 41 3 t4 5 2tA 23A 25...

Page 150: ...6a b Two Main 4 Ply Rating Tires 6 00 6 with Regular Tubes Cert Basis TSO C62 One Nose Wheel a Cleveland Aircraft Products Wheel Assembly No 40 768 Less Brake Drum Cert Basis TSO C26a b McCauley Indus...

Page 151: ...o q a Item No 39A 41 A c Landing Gear and Brakes cont Item Handlrake Master Cylinder Piper Dwg 65842 Cleveland Aircraft Products No 10 22 Toe Brake Cylinders a Cleveland Aircraft Prgduct Ne 10 27 b Ga...

Page 152: ...y Piper Dwg 76454 Rebat S 25 Starter Relay Piper Dwg 99130 2 RBM Controls P N I I l l I l Mark if Instl Weight Pounds Arm ln Aft Datum 5t 9 r68 0 45 8 80 2 Moment Lb ln 47 3679 5tA 538 55A 57A 59A Ove...

Page 153: ...i i 1Z Por z z o FJ o 93 1 Et N QO r io A F g AF r t E 37 67 54 43 50 50 60 9 0 9 0 8 h a e c F tJ o I 698 7tB 73A 75A 771 194 Compass Cert Basis TSO C7c Tachometer Piper Dwg 62177 14 Engine Cluster...

Page 154: ...23 f Miscellaneous Item Forward Seat Belts 2 Piper Spec PS50039 4 2A American Safety Eqpt Corp 500576 Davis Acft Prod Inc FDC 5900 12G5 Black Cert Basis TSO C22f Rear Seat Belts 2 Piper Spec PS50039...

Page 155: ...r Harness 2 Front Seats Only Piper PS50039 Pacific Scientific PIN I107447 13 Black b Shoulder Harness Fixed Front 2 Piper PS50039 4 23 American Safety Eqpt Corp 501385 2107 Davis Acft Prod Inc FDC 727...

Page 156: ...6Z r ar No F H EE I O B b J e Item No Item g Engine and Engine Accessories Optional Equipment Item h Propeller and Propeller Accessories Optional Equipment Item Mark if Instl Mark if Instl Weight Pou...

Page 157: ...ot 6X rg OF E FI Fi z a a FI c F br o o i Landing Gear and Brakes Optional Equipment Item Mark if Instl Weight Pounds Arm In Aft Datum Moment Lb In Item No t25 t27 Fairing 37896 3 Nose Wheel Piper Dwg...

Page 158: ...rument Panel Lights Piper Dwg 76454 Instrume nt or Whelen Light Grimes 154083 7 A300 w t4 Mark if Instl Weight Pounds Arm ln Aft Datum o 8 99 0 99 0 t3 r t05 6 Moment Lb ln 0 3 0 1 0 3 0 5 0 4 5 8 Cab...

Page 159: ...e With Red Strobe Whelen Model A600 Navigation Lights Wing 2 Red White Greenl White Whelen Model A675 Navigation Light Rear l Grimes Model 2064 White Mark if lnstl Weight Pounds Arm In Aft Datum Momen...

Page 160: ...lcc Pump b With Edo Aire Model lUl28A Pump Attitude Gyro Piper Dwg 99002 2 3 4 or 8 Cert Basis TSO C4c Directional Gyro Piper Dwg 99003 2 3 4 or 7 Cert Basis TSO C5c 4 5 4 9 39 I 39 I x 2 2 59 4 2 6...

Page 161: ...Cert Basis TSO C88 Vertical Speed Piper Dwg 99010 2 4 or 5 Cert Basis TSO C8b Alternate Static Source Piper Dwg 35493 Turn and Slip Indicator Piper PS50030 2 or 3 Cert Basis TSO C3b Exhaust Gas Tempe...

Page 162: ...re Gauge Piper Dwg 99479 0 or 2 Mark if Instl Mark if Instl Weight Pounds 0 2 Weight Pounds 5 6 Moment Lb In l5 Moment Lb In Arm ln Aft Datum 72 6 Arm In Aft Datum l Autopilots Optional Equipment Item...

Page 163: ...sceiver a Single b Dual Cert Basis TSO C37b C38b Collins VIR 350 or VIR 351 Nav Receiver a Single b Dual Cert Basis TSO C40a C36c Collins IND 350 VOR LOC Indicator a Single b Dual Cert Basis TSO C40a...

Page 164: ...l Mark if lnstl Weight Pounds t2 0 Weight Pounds t 0 Arm In Aft Datum 69 0 Arm ln Aft Datum Moment Lb In 828 Moment Lb ln Autopilot Century 2l Piper Dwg 39726 Cert Basis STC SA3352SW m Radio EquiPment...

Page 165: ...0a Bendix CN 2013 4 ComlNav w G S Receiver M B Receiver Bendix ADF 2070 Cert Basis TSO C4lc C2a Bendix TR2060 Transponder Cen Basis TSO C7 k Bendix CN 201I Dual Com Nav Cert Basis TSO C34c C35d C37b C...

Page 166: ...ollins VHF 250 or VHF 251 Comm Transceiver a Single b Dual Cert Basis TSO C37b C38b Collins VIR 350 or VIR 35t Nav Receiver a Single b Dual Cert Basis TSO C l0a C36c Collins IND 350 VORi LOC lndicator...

Page 167: ...rm ln Aft Datum t8l E t l4 9 5r 9 t04 8 25t 253 255 257 259 Item Collins IND 351 vOR LOC cS lndicator Cert Basis TSO C40a C36c Collins GLS 350 Clidc Slope Receiver Cen Basis TSO C34c Collins DME 451 w...

Page 168: ...dio Marker Panel Cert Basis TSO C35d C50b Collins TDR 950 Transponder Cert Basis TSO C74c King KN 53 Nav Receiver King KN 53 Nav Receiver wlG S Receiver a Single b Dual Weight includes antenna and cab...

Page 169: ...SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION P4 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1120 6 31a ISSUED JUNE 25 1981...

Page 170: ...mm Nav Receiver a With Audio Amplifier b With Glide Slope Receiver c Without Glide Slope Receiver Cert Basis TSO C37b C38b C40a C36a King KX 165 VHF Comm Nav Receiver a With Glide Slope Receiver b Wit...

Page 171: ...Transceiver b King KN 72 VOR LOC Converter c King KN 75 Glide Slope Receiver d King KI 204 VOR lLS lndicator Cert Basis TSO C36c C37b C38b C40a King KX 175 VHF a Transceiver 2nd b King KN 72 VORi LOC...

Page 172: ...ngle b Dual Cert Basis TSO C37b C38b King KY 197 Transceiver Cert Basis TSO C37b C38b a Single b Dual King KI 202 VOR LOC Indicator Cert Basis TSO C40a C36c King KI 206 VOR LOC Indicator Cert Basis TS...

Page 173: ...a King KN 62A DME King KR 85 Digital ADF a Audio Amplifier Ceit Basis TSO C4lb King KR 65 ADF with KA 42B Loop and Sense Antenna a Audio Amplifier Cert Basis TSO C4lb King KR 86 ADF a First b Second c...

Page 174: ...b Second c Audio Amplifier 7 6 10 6 0 8 91 6 107 0 5r 0 4 0 2 8 3 6 0 8 59 0 t47 4 150 6 5r 0 Mark if Instl Weight Pounds 3 1 Arm In Aft Datum 70 8 Moment Lb In 696 tt34 4l 236 413 542 4l 262 King KR...

Page 175: ...King KT 76 73 X Transponder Cert Basis TSO C74b King KRA 10 Radio Altimeter 30r Narco Comm 120 VHF Transceiver a Single b Dual Cert Basis TSO C37b C38b 303 Narco Nav l2l VHF Receiver a Single b Dual...

Page 176: ...F Receiver a Single b Dual Cert Basis TSO C34c C35d C36c C40c C66a 309 Narco Nav l24A VHF Receiver a Single b Dual Cert Basis TSO C35d C36c C40a C66a 3ll Narco lD 124 VOR LOC GS Indicator a Single b D...

Page 177: ...dio Selector Panel Cert Basis TSO C50b Narco CP 135M Audio Selector Panel Cert Basis TSO C50b C35d 4 2 8 4 154 0 220 0 647 I 848 2 2 55 0 l2l 3 7 I14 3 423 5 9 60 9 359 13 2 154 5 2039 Mark if Instl W...

Page 178: ...Antenna and Cable a Nav Receiving VRP 37 or AV I2PPR b l VHF Comm PS50040 18 c 2 VHF Comm PS50040 18 d ADF Sense STD 99841 e ADF Sense All Weather 79160 328 Marker Beacon Antenna Piper PS50040 15 Kin...

Page 179: ...Model ELT 10 a Antenna and Coax b Shelf and Access Hole Microphone a Piper Dwg 68856 10 b Piper Dwg 68856 ll c Piper Dwg 68856 12 Boom Microphone Headset Piper Dwg 37921 2 Cabin Speaker Piper Dwg 9922...

Page 180: ...r 03 6 t 48 9 t68 5 t56 0 Moment Lb ln 790 7476 849 2393 2tr I 405 407 409 4il 413 4t5 4t7 Item Zinc Chromate Finish Piper Dwg 797W 2 Stainless Steel Control Cables Piper Dwg 79700 Air Conditioner Pi...

Page 181: ...wg 79591 l 79591 1 Headrests 2 Front Piper Dwg 79337 18 6 6 ttO 7 6 tt t 0 0 2 2 94 5 2 2 t32 l 1 6 t40 3 224 5l 3 544 208 291 FI U lrl 17A a l ai 7 O b Oo J Headrests 2 Rear Piper Dwg 79337 18 lncrti...

Page 182: ...Inc FDC 7275 162 Black Shoulder Harness Inertia Rear 2 Piper PS500394 19 Pacific Scientific 1rc7 447 4l Black Assist Strap Pipcr Dwg 79455 Item 431 Mark if lnstl Weight Pounds Arm In Aft Datum Moment...

Page 183: ...Optional Equipment cont 445 Item Fire bxtinguisher a Piper Dwg 76167 2 Scott 4221 l 00 b Piper Dwg 37872 2 Graviner HAl0l4 01 Locking Gas Cap Piper Dwg 39830 2 tWeight and moment difference between st...

Page 184: ...e Airtiame Engine and Propeller Engine Controls Electrical System Vacuum System Instrument Panel PitotStatic System Heating and Ventilating System Cabin Features Baggage Area Stall Warning Finish Air...

Page 185: ...No Paragraph REPORT VB 1120 7 ii TABLE OF CONTENTS SECTION 7 cont THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 186: ...il The wings are attached to each side of the I uselage by insertion of the butt encls of the respective main spars into a spar box carry through which is an integral part of the fuselage structure pr...

Page 187: ...SECTION 7 DESCRIPTION OPERATION PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II e j _ MAIN WHEEL ASSEMBLY Figure 7 1 RIIPORT VB 1120 7 2 ISSUED JULY 2 1979...

Page 188: ...h side of center A shimmy dampener is also included in the nose gear The three struts are of the air oil type with a normal extension of 3 25 inches fclr the nose gear and 4 50 inches for the main gea...

Page 189: ...SECTION 7 DESCRIPTION OPERATION PIPER AIRCRAFT CORPORATION PA 28 I81 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORN VB 112O 7 4 ISSUED IALY 2 1979...

Page 190: ...tween the front seats Figure 7 3 A rudder trirn adjustment is mounted on the right side of the pedestal below the throttle quadrant and permits directional trim as needed in 1ight rel er to Figure 7 5...

Page 191: ...SECTION 7 DESCRIPTION OPERATION PIPER AIRCRAFT CORPORATION PA 28 18I ARCHER II CONTROL QUADRANT AND CONSOLE Figure 7 5 REPORT VB 1120 7 6 ISSUED JULY 2 1979...

Page 192: ...e carburetor heat control lever is located to the right o the control quaclrant on the instrument pancl Thc control is placarded with two positions ON down OFF up 7 13 FUEL SYSTEM Fuel is storecl in t...

Page 193: ...he lire wall has a drain which is accessible liom outside the nose section The strainer should also be drained before the first flight of the day Refer ro paragraph 8 21 lbr the complete lirel drainin...

Page 194: ...PRIL 2 1998 n FUELOUANTITY GAUGES F UEL SYSTEM SCHEMATIC Figure 7 9 7 15 ELECTRICAL SYSTEM The electrical system includes a 14 volt 60 amp alternator a 12 volt battery a voltage regulator an overvolta...

Page 195: ...ical load and a fully charged battery the Alternator Inop Light rnay illuminatc due to minimal altemator output If the altemator is iunctional a slight increase in electrical load should extinguish th...

Page 196: ...7 DESCRIPTION OPERATION rxttt a tDtl I I rl Ieaa nlE snat I E rtl r F n 1 I wfaa I rllx ntF I tntll tattftll ISSUED JALY 2 1979 REVISED JANUARY 14 1981 Itaxo tr l lf ff F rl REPORT VB L1 20 7 tL Hita...

Page 197: ...es not indicate battery discharge rather it displays in amperes the load placed on the aiternator With all electrical equipment off except master switch the ammeter will be indicating the amount of ch...

Page 198: ...necessary plumbing The vacuum pump is a dry type pump which elirninates the need for an airloil separator and its plumbing A shear drive protects the pump from damage If the drive shears the gyros wil...

Page 199: ...to the avionics bus in event of a radio master switch circuit t ailure The ernergency bus switch is located behind the lower right shin guard leti of the circuit breaker panel An engine cluster is loc...

Page 200: ...e 9 6rd i it i FFgsgE gg SSIBBBBgE Fg 2r_ uG Eg OG 5r i n IIEEi EEEi J iiiaridF toa daadd ddddo d Elgissftis i iadoF oici Fd B sI 6o eqi lE i E iEIsEEi HFggEE i33 ciri rirtr doo INSTRUMENT PANEL Figur...

Page 201: ...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 Thc altimeter error is less than 50 t ee...

Page 202: ...II SECTION 7 DESCRIPTION OPERATION I I t I ALTIMEICi 2 AIRSFEEO INOCAIOi flror HrAT SWIGX a vtRncAL sPC O ltaolcAtoS 6 FTOT IGAD 6 OfiAllr vA ts r alrf ix rf stAnc soJncE PITOT STATIC SYSTEM Figure 7...

Page 203: ...8rEn xrnar t l owEiswrcH t t t ocfiosrErcoxllol ro tlc rcicoffrnot il g lr f rmrEf s rI coirnor 12 FnESHAncolltnor o t ricsHAtitEr 2 HI CY DUGT 3 riEst Alt irowEn a e rutc DASSCXILY 6 rrESH Ati Ot gt...

Page 204: ...le cln models without ait 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 burn...

Page 205: ...he rear occupants Shoulder harnesses should be routinely worn during takeoff landing and whenever an inflight emergency situation occurs 7 27 BAGGAGEAREA A 24 cubic fbot baggage area located behind th...

Page 206: ...e air conditioner is ON and fetracts to a flush position when the system is OFF The cornpressor is mounted on the forwarcl right underside of the engine It has an electric clutch which automatically e...

Page 207: ...icator light is located to the left of the radio stack in fiont of the pilot The light illuminates whenever the condenser door is open and remains on until the door is closed A circuit breaker located...

Page 208: ...battery must be replaced on or before this date The battery must also be replaced if the transmitter has been used in an emer gency situation or if the accumulated test time exceeds one hour or if th...

Page 209: ...oving the switch to ARM A pilot s remote switch locatecl on the lelt side panel is provicled to allow the transmitter to be turned on li om inside the cabin The pilot s remote switch is placarded ON a...

Page 210: ...e reset by either positioning the remote switch to the ON position for two seconds and then relocating it to the ARM positi0n or by setting the switch on the ELT to OF F and then back to ARM In the ev...

Page 211: ...er is activated by an impact it can be turnecl off by rnoving the ELT switch OFF Normal operation can then be restored by resetting tho switch to ARM It may also be turned olT and reset by positioning...

Page 212: ...r heat Relbr to Pzu agraph 3 29 Carburetor Icing in the emergency procedures To adjust the system for critical ice detection first turn on the airplanes master switch and then turn on the ice detectio...

Page 213: ...SECTION 7 DESCRIPTION OPERATION PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB L120 7 28 ISSUED IULY 2 1979 REVISED MARCH 29 1994...

Page 214: ...General Airplane Inspection Periods Preventive Maintenance Airplane Alterations Ground Handling Engine Air Filter Brake Service Landing Gear Service Propeller Service Oil Requirements Fuel System Tir...

Page 215: ...No Paragraph REPORT VB 1 120 8 ii TABLE OF CONTENTS SECTION 8 HANDLING SERV MAINT THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 216: ...to time issues service releases including Service Bulletins Service Lettels and Service Spares Letters and others relating to the airplane Service Bulletins are of special importance and Piper conside...

Page 217: ...le and qualified mechanic at a Piper Authorized Service Center or a reputable repair shop Piper Aircraft Corporation cannot accept responsibility for the continued airworthiness of any aircrafi not ma...

Page 218: ...ormed only on an aircraft which the pilot owns or operates and which is not used to carry persons or property for hire except as proviclecl in applicable FAR s Although such maintenance is allowed by...

Page 219: ...craft a To be displayed in the aircraft at all times 1 Aircrafi Airworthiness Certificate Form FAA 8100 2 2 Aircrafi Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station License if transm...

Page 220: ...rporated as part of the nose gear fbrk CAUTION When towing with power equipment do not tuln the nose gear beyond its steering radius in either direction as tltis will result in damage to the nose gear...

Page 221: ...he airplane 4 When taxiing over uneven ground avoid holes and ruts 5 Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones gravel or any loose naterial t...

Page 222: ...and pulling it snug 4 Block the whesls 5 Secure tie down ropes to the wing tie down rings and to the tail skid at approximately 45 degree angles to the ground When using rope of non synthetic materia...

Page 223: ...it immediately 3 Wipe the filter housing with a clean cloth and insrall the fllter The usable life of the lilter should be restricted to one year or 500 hours whichever comes first c Installation Of...

Page 224: ...D FI DD R P DAI 4 RIGXI ARAKf CYIINOFR 5 t FI SFAKF CYiINOER 6 6RAXF HATIOLE 7 HAt Dt t ocx EUItoN fi I rNr rilr tl I rir Fvls PIN IO MAS1FII YTINI FII ASSTMBLY tt BottAssgMBlY t roR UF rltEE l3 oPll...

Page 225: ...e strut to full compression If the strut has sufficient fluid it will be visible up to the bottom of the liller plug hole and will then require only proper inf lation Shoulcl f luicl be below the bott...

Page 226: ...als and rudder are centered Alignrnent of the nose wheel can be checked by pushing the aiI plane back ancl forth with the ruclder centered to detertnine that the plane follows a perfectly straight lin...

Page 227: ...ap indicated ranges use the lighter grade oil l NOTE Rel er to the latest issue oi Lycorning Service Instruction 1014 Lubricating Oil Recom mendations for further inforrnation 8 21 FUEL SYSTEM a Servi...

Page 228: ...When an anti icing additive is used it must meet the specification MIL I 27686 must be uniformly blended with the ftrel while refueling must not exceed l5Vo t y volume of the refueleil quantity urnd t...

Page 229: ...s and Lines The fuel system sumps and strainer should be drained daily prior to the first flight and after ref ueling to avoid the accurnulation of contaminants such as water or sediment Each fuel tan...

Page 230: ...it has closed completely and is not leaking e Draining Fuel System The bulk of the f uel may be drained from the system by opening the valve at the inboard end of each fuel tank Push up on the arms of...

Page 231: ...king tire pressure examine the tires for wsar cuts bruises and slippage 8 25 BATTERY SERVICE Access to the 12 volt battery is through an access panel at the right rear side of the baggage compartment...

Page 232: ...xture of solvent and degreaser In order to lemove especially heavy dirt and grease de posits it rnay be necessary to brush areas that were sprayed CAUTION Do not spray solvent into the altcrnator vacu...

Page 233: ...rt c Cleaning Exterior Surfaces The airplane should be washed with a mild soap and water Harsh abrasives or alkaline soaps or cletergents could make scratches on painted or plastic surf aces or could...

Page 234: ...rl aces apply a thin coat of hard polishing wax Rub lightly with a soft cloth Do not use a circular motion 5 A severe scratcl t or rlar in plastic can be removed by rub bing out the scratch with jewel...

Page 235: ...ON For cold weather operation a winterization plate is installed on the inlet opening of the oil cooler duct on the right rear engine baffle This plate should be installed whenever the ambient tempera...

Page 236: ...ook Revision Only This Is Not A Completc Hand hook REPOM VB 120 Rcv 16 PR980402 Dated April 2 1998 This revision shall be inserted into the current PA 28 18l Archer II Pilot s Oporating Handbook REPOR...

Page 237: ......

Page 238: ...Piper Electric Pitch Trim Century 21 Autopilot Installation Piper Control Wheel Clock Installation King KAP 100 Series Flight Contol System King KAP 150 Series Flight Control System KNS 80 Navigation...

Page 239: ...Paragraph No REPORT VB 1120 f ii TABLE OF CONTENTS SECTION 9 SUPPLEMENTS THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 240: ...he airplane when equipped with one or more of the various optional systems and equipment not approved with the standard airplane All of the supplements provicled in this section are FAA Approvecl and...

Page 241: ...S BCTION 9 SUPPLEMENTS PIPER AIRCRAFT CORPORATION PA 28 I81 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORI VB 1120 a t ISSUED JULY 2 1979...

Page 242: ...all times when the optional air conditioning system is installed SECTION 2 LIMITATIONS a To insure tnaximum climb performance the air conditioner must be turned OFF manually prior to takeoff to disen...

Page 243: ...oner condenser door is in the up position d If the AIR COND DOOR OPEN light does nor respond as specified above an air conclitioner system or indicator bulb mal function is indicated and f urther inve...

Page 244: ...The decrease in range may be as much as 32 nautical miles for the 48 gallon capacity The clirnb performance is not compromised measurably with the air conditioner operating since the compressor is de...

Page 245: ...SECTION 9 SUPPLEMENTS PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1120 9 6 ISSUED JULY 2 1979...

Page 246: ...the optional AutoFlite II Autopilot is installed SECTION 2 LIMITATIONS a Autopilot use prohibited above 149 KIAS b Autopilot OFF during takeoff and landing SECTION 3 EMERGENCY PROCEDURES a In case of...

Page 247: ...ading Changes l Depress Disconnect Switch make Heading Change release Disconnect Switch 2 Move Trim Knob on instrument for Drift Correction l rom a constant heading 3 Move Turn Command Knob on instrum...

Page 248: ...installed SECTION 2 LIMITATIONS a Autopilot use prohibited above 149 KIAS b Autopilot OFF cluring takeoff and landing SECTION 3 EMERGENCY OPERATION a In an emergcncy the AutoControl IIIB can be discon...

Page 249: ...nd HDG switches Set HDG bug to aircraft heading and rotate O B S to cause OMNI indicator Needle to swing left and right slowly Observe that control wheel rotates in direction of needle movement 2 Dise...

Page 250: ...e the localizer frequency and place the HDG bug on the inbound fi ont course heading Select LOC NORM mocle on the coupler and HDG mode on the autopilot console 3 FoI LOC Back Course Intercepts and Tra...

Page 251: ...SECTION 9 SUPPLEMENTS PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORI VB 1120 9 12 ISSUED JALY 2 1979...

Page 252: ...rnes when the optional Piper Electric Pitch Trim is installed SECTION 2 LIMITATIONS No changes of the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this...

Page 253: ...erating the trim control switch on the pilot s control yoke To prevent excessive speed increase in the event of an electric trim runaway malfunction the system incorporates an automatic disconnect fea...

Page 254: ...this handbook and must remain in this handbook at all times when the optional Century 21 Autopilot is installed SECTION 2 LIMITATIONS a Autopilot operation prohibited above 147 KIAS b Autopilot OFF du...

Page 255: ...aved NSD 360A a Appearance of HDG Flag 1 Check air supply gauge vac or pressure for adequate air supply 4 in Hg min 2 Check compass circuit breaker 3 Observe display fbr proper operation b To clisable...

Page 256: ...ows may remain out of view depending upon the design of the NAV converter used in the instal lation SECTION 4 NORMAL PROCEDURES Refer to Eclo Aire Mitchell Century 21 Autopilot Operator s Manual P N 6...

Page 257: ...ovide only slave and liee gyro positions 2 Rotate card to center slaving meter check HDG displayed with magnetic compass HDG 3 Perform standard VOR receiver check 4 Perfbrm Steps 1 7 in Section 4 item...

Page 258: ...t of this handbook and must remain in this handbook at all times when the optional Piper Control Wheel Clock is installed SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section...

Page 259: ...d the time displayed At the time mark the ST SP button is pressed momentarily to begin the time counting at the exact second If the rninutes are not advanced when they are flashing in the set mode pre...

Page 260: ...talled in accordance with STC SA1565CE D The information contained herein supplements or supersedes the infor mation in the basic Pilot s Operating Harrdbook and FAA Approved Airplane Flight Manual on...

Page 261: ...ies Flight Control Sysrem is installed SECTION 2 LIMITATIONS The autopilot must be OFF during takeoff and landing SECTION 3 EMERGENCY PROCEDURES a SYSTEM WITH AUTOPILOT ONLY l In case of Autopilot mal...

Page 262: ...ctuate the left side of the split switoh to the fore and aft positions The trim wheel should not move on its own Rotate the trim wheel manually against the engaged clutch to check the pilot s overpowe...

Page 263: ...ut of trim condition b Heading Hold 1 Heading Selector Knob SET BUG ro desired heading 2 HDC Mode Select or Button PRESS Note HDG mode annunciator ON Autopilot will automatically turn the aircraft to...

Page 264: ...nob SELECT desired course 2 NAV Mode Selector Button PRESS 3 Heading Selector Knob ROTAIE BUG to agree with OBS course NOTE When NAV is selected the lateral operating mode will change fiom HDG if sele...

Page 265: ...re point is reached the HDG will disengage the APR annunciator will illumi nate steady and the selected course will be auto rnatically captured and tracked If the D Bar is Iess than 2 to 3 dots the HD...

Page 266: ...S front course inbound heading NOTE When equipped with NAV I NAV 2 switching and NAV 2 is selected set OBS to the ILS front course inbound heading 2 HEADINC Selector Knob SET BUG to provide desired in...

Page 267: ...ss HDG not selected and BC modes with APR flashing when the computed capture point is reached the HDG annunciator will go out the BC and APR annunciators will illurninate steady and the selected cours...

Page 268: ...arious instruments and the controls fbr the operation of the KAP 100 Autopilot are described in Figures 7 1 thru 7 I 1 The KAP 100 Autopilot has an optional electric pitch trim system The trirn system...

Page 269: ...Iliurninates continuously whenever trim power is not on or the system has not been pre flight tested The TRIM warning light will flash and be accom panied by an audible warning whenever a manual pitch...

Page 270: ...d will select the Approach mocle This mode provides all angle intercept with HSI or a fixed angle intercept of 45 with DG automatic beam capture ancl tracking of VOR RNAV or LOC signals The tracking g...

Page 271: ...SCALE Moves with respecr to the symbolic airplane to present pitch attitude Scale graduated at 0 5 10 I5 20 and 25 degrees 5 SYMBOLIC AIRPLANE Serves as a stationary symbol of the aircraft Aircraft pi...

Page 272: ...receiver signal is in adequate When a NAV flag is present in the navigation indicator CDI or KI 525A the autopilot operation is not affected The pilot must monitor the navigation indicators tor NAV tl...

Page 273: ...e beam centerline 9 RECIPROCAL COURSE INDEX Inclicates reciprocal of se lected VOR course 10 OMNI BEARING SELECTOR OBS KNOB Rorares course card to selected course 11 COURSE DEVIATION NEEDLE Indicates...

Page 274: ...rd 10 The selected VOR radial or localizer heading remains set on the compass card when the compass card 10 rotates 6 TO FROM INDICATOR FLAG Ittdicates direction of VOR station relative to selected co...

Page 275: ...ation bar displace ment of 5 dots represents full scale VOR 10o LOC 2 I 2o RNAV 5NM RNAV APR 1 1 4NM deviation fiom beam centerline 14 HEADING BUG Moved bV tl knob 9 to select desired heading 3 4 KG 1...

Page 276: ...tes to display heading of airplane with reference to lubber line 2 5 HEADING SELECTOR KNOB F Positions heading Bttg 3 on compass catd 4 by rotating the heading selector knob The Bug rotates with the c...

Page 277: ...lutch and the right half to control the direction of motion of the trim servo motor Both halves of the split trim switch tnust be actuated in order for the manual trim to operate in the desired direct...

Page 278: ...er to the avionics bus bar of the radio circuit breakers and the autopilot oircuit breaker The fbllowing circuit breakers are used to protect the following elements o1 the King KAP 100 Autopilot AUTOP...

Page 279: ...SECTION 9 SUPPLEMENTS PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1120 9 40 ISSUED JULY 21 1982...

Page 280: ...alled in accordance with STC SA156 5CE D The information contained herein supplements or supersedes the infor nlation in the basio Pilot s Operating Handbook and FAA Approved Airplane Flight Manual on...

Page 281: ...2 LIMITATIONS a During autopilot operation a pilot with seat belt f astened must be seated at the left pilot position b The autopilot must be OFF during takeofT and landing c The system is approved f...

Page 282: ...ilot malfunction Configuration Alt Loss Cruise Climb Descent Maneuvering APPR 310 90 85 SECTION 4 NORMAL PROCEDURES a PREFLIGHT PERFORM PRIOR TO EACH FLIGHT 1 GYROS Allow 3 4 minutes for gyros to come...

Page 283: ...NLY ENGAGE by pressing FD or CWS button 6 AUTOPILOT ENGAGE by pressing AP ENG bumon 7 CONTROL WHEEL MOVE fore aft left and right to verify that the autopilot can be overpowered 8 AP DISC TRIM INTER Sw...

Page 284: ...fly aircraft to desired pressure altitude CWS Button RELEASE when desired pressure altitude is reached The autopilot will maintain the desired prossure altitude 2 Using Vsrtical Trirn Recommended for...

Page 285: ...et OBS to the desiled course 2 HEADING Selector Knob SET BUG to provide desired intercept angle 3 NAV Mode Selector Button PRESS If the Course Deviation Bar is greater than 2 to 3 dots the aircratt wi...

Page 286: ...than 2 to 3 dots the HDG mocle will disengage upon selecting NAV mode the NAV annun ciator will illuminate steady and the capture track sequence will automatically begin 7 Approach APR Coupling a When...

Page 287: ...on the position of the bug If the D Bar is greater than 2 to 3 dots the autopilot will annunciate HDG mode unless HDC not se lected and APR llashing when the computed capturs point is reached the HDG...

Page 288: ...BC annunciator will illuminate steady and the capture track sequence will autornatically begin b When ecluipped with DG L OBS Knob SELECT the ILS front course inbound heading 2 BC Mode Selector Butto...

Page 289: ...ENGAGED b At glide slope centering NOTE GS annunciator ON NOTE Autopilot can capture glide slope from above or below the beam while operating in either pitch attitude hold or ALT hold modes 10 Missed...

Page 290: ...weight and balance data in Section 6 of the basic Pilot s Operating Handbook SECTION 7 DESCRIPTION AND OPERATION The 150 Series AFCS is certified in this airplane with 2 axis control pitch and roll Th...

Page 291: ...With the HDG flag present the Autopilot may be re engaged in the basic wings level mode along with any vertical rnode d Roll rates in excess of 16 per second rvill cause the autopilot to disengage exc...

Page 292: ...trim fault is detected The TRIM warning light will illuminate steady and be accompanied by a steady audible tone whenever an autotrim failure occurs The autotrirn system is monitored for the followin...

Page 293: ...ect the Heading mode which commands the air plane to turn to and maintain the heading selected by the heading bug on the DG or HSI A new heading may be selected at any time and will result in the airp...

Page 294: ...orresponcling mode selector button PUSH ON PUSH OFF or when tfe glide slope GS mode is automatically engaged 4 GLIDE SLOPE GS ANNUNCiATOR Illuminates continuously whenever the autopilot is coupled to...

Page 295: ...t 8 PREFLIGHT TEST TEST BUTTON When nomenrarily pushed initiates preflight test sequence which automatically turns on all annunciator lighis tests the roll ancl pitch rate monitois tests the autotrim...

Page 296: ...rnmands the air plane to turn to and maintain the heading selected by the heading bug on the DG or HSL A new heading may be selected at any time and will result in the airplane turning to the new heac...

Page 297: ...15 20 and 25 degrees 5 COMMAND BAR Displays computed steering commands referenced to the symbolic airplane The command bar is visible only when FD mode is selected The command bar will be biased out o...

Page 298: ...th respect to the symbolic airplane to present pitch attitude Scale graduated at 0 J 110 lJ 20 and 25 degrees 5 SYMBOLIC AIRPLANE Serves as a stationary symbol of the aircraft Aircraft pitch and roll...

Page 299: ...on indicator CDI or KI 525A the autopilot operation is not affected The pilot must monitor the navigation indicators fbr NAV flags to insure that the Autopilot and or Flight Director are tracking vali...

Page 300: ...eam centerline 9 HEADING SELECTOR KNOB tI Positions heading bug 14 on compass card 10 by rotating the heading selector knob The Bug rotates with the compass card 10 COMPASS CARD Rotates to display hea...

Page 301: ...ct desired headi ng 4 COMPASS CARD Rotates to display heading of airplane with ret erence to lubber line 2 on DG 5 HEADING SELECTOR KNOB 3 on compass card 4 by rotating Bug rotates with the compass ca...

Page 302: ...is present in the navigation indicator CDI or KI 525A the autopilot operation is not aff ected The pilot must monitor the navigation indicators for NAV flags to insure that the Autopilot and or Fligh...

Page 303: ...or below glicle slope beam centerline 9 RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR course 10 OMNI BEARING SELECTOR OBS KNOB Rotates course card to selected course 11 COURSE DEVIATION...

Page 304: ...omatically disconnect the autopilot 3 CONTROL WHEEL STEERING CWS BUTTON When depressed allows pilot to manually control the aircraft disengages the servos without cancellation of any of the selected m...

Page 305: ...ss bar of the radio circuit breakers and the autopilot circuit breaker The tbllowing circuit brcakers are used to protect the following elements of the King 150 Series Autopilot AUTOPILOT Supplies pow...

Page 306: ...omplete handbook This supplement has been FAA Approved as a permanent part of this handbook and must remain in this handbook at all times when the optional KNS 80 Navigation System is installed SECTIO...

Page 307: ...cause the systern to alternate between the VOR and VOR PAR modes while repetitive pushing of the RNAV button causes the systenl to alternate between RNV ENR and RNV APR modes b coNTRoLS 1 VORBUTTON M...

Page 308: ...curs from the units to the tens position Rollover occurs tiorn 117 to 108 or vice versa Center knob varies frequency in 05 MHz steps regardless ol whether the switch is in its in or out position b Rad...

Page 309: ...IRCRAFT CORPORATION PA 28 1 81 ARCHER II SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement REPORT VB...

Page 310: ...led irr accordance with Piper Drawing 87174 2 The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane FIight Manual only in those areas list...

Page 311: ...4 8 in Hg 3 The auxiliary purnp rnotor assembly and elapsed time indicator must be removed from service al ter 500 hours accumulated operating tirne or 10 years whishever occurs first SECTION 3 EMERGE...

Page 312: ...uum pump and verity AUX ON light goes out B Inflight Check Prior to entering instrument flight conditions l Turn ofT non essential electrical equipment 2 Turn on auxiliary vacuum pump and verify AUX O...

Page 313: ...F F section is controlled by a vacuuin switch in the prirnary pneumatic systcln and illurninates an amber liglif when thg engine driven pump is inoperative or whcn the systcm vacuum lalls below the sw...

Page 314: ...3 6i s WA J oY O Pb St EEFSH r crioid UJ F U E 1 x ul q E E IL 9 I I O F o v o_ z a 2 6 a 223 g tZitttu r O uliGrn r3E 3 EH j 2e ns6HiE ddc 6 si E FHH3 58dafi5 6 xSbd ZlrJe uJa L c i t i rtto o 9 I r...

Page 315: ...SECTION 9 SUPPLEMENT 10 PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1120 9 76 ISSUED OCTOBER 20 1986...

Page 316: ...ion System is installed per Equipment List The infbrmation contained herein supplements or supersedes the infbrmation in the basic Pilot s Operating Hanclbook ancl FAA Approved Airplane Flight r anual...

Page 317: ...is handbook at all times when the optional Bendix King KLN 90 GPS Navigation System is installed SECTION 2 LIMITATIONS a CPS limited to VFR use only b The following placard is located on the pilots in...

Page 318: ...t annunciator will begin llashing TIis is called waypoint alerting 2 Message MSG MSG will llash to alert the pilot o a situation that requires attention Press the MSG button on the KLN 90 GPS to view...

Page 319: ...SECTION 9 SUPPLEMENT 11 PIPER AIRCRAFT CORPORATION PA 28 181 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1120 9 80 4of4 ISSUED JANUARY 07 1993...

Page 320: ...Flight Manual when the Precise Flight Pulselite system has been installed in accordance u ith STC SA4OOsNM The infor mation contained in this document suppl s or supersedes the basic manual only in t...

Page 321: ...nual for the model number installed The Pulselitee System is consider ed optional equiprnent and the aircraft rnay be dispatched with the system turned OFF In case of a system rnalfunction the circuit...

Page 322: ...n accordance with STC s sA2160NM SA2 l 6lNM SA2162NM SA2164NM SA2l67NM SA21 68NM 542683NM Aircraft SEI779NM Lycoming Engine sE1 78oNM clltin ntut rngin The information contained in this document suppl...

Page 323: ...e system to drive your flight instruments CAUTION The use of the Standby Vacuum System requires a degree of Pilot skill and proficiency that is best maintained through practice lt is recommended upon...

Page 324: ...um powered or vacuum gyro directed autopilot should be OFF when operating with a failed primary vacuum system 3 The SupplementalVacuum System is not designed to operate pneumatic de ice systems DO NOT...

Page 325: ...the push pull control cable Placard to be located around the LED for the pump inop warning light Placard to be placed in front and in full view of the pilot STANDBY VACUUM SYSTEM EQUIPPED FOR OPERATI...

Page 326: ...Vacuum Available Altitude Power Chart for aircraft with Constant Speed Propeller Maximum Continuous RPM Approximate Standby Vacuum Available Altitude Power Chart for aircraft with a Fixed Pitch Propel...

Page 327: ...ORE TAKEOFF a ldle Engine at low speed momentarily pull the standby vacuum knob OUT ON and check vacuum gauge Normally the vacuum reading will be slightly higher After checking system push Standby Vac...

Page 328: ...re Vacuum power must be closely monitored by checking the vacuum gauge frequently b The SVS is not designed for continued IFR flight lmmediate steps should be taken to return to VFR conditions or to l...

Page 329: ...ts Reapply power as required while comparing vacuum driven gyros against the Turn and Bank lndicator Turn Coordinator VSI and or other flight instruments When an obvious discrepancy is noted between t...

Page 330: ...TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph No 10 1 General 10 3 Operating Tips Page No 10 1 10 1 REPORT VB 1120 10 i...

Page 331: ...No Paragraph REPORT VB 1120 10 ii TABLE OF CONTENTS SECTION 10 cont THIS PAGE INTENTIONALLY LEFT BLANK Page No...

Page 332: ...esirable to have tire airplane at a slower speed before extending the flaps The flap step will not support weight if the flaps are in any extended position The flaps must be placecl in the UP position...

Page 333: ...s advisoly circulars Aviation News AIM and safety aids i Prolonged slips or skids which result in excess of 2000 ft of altitude loss or other radical or extreme maneuvers which could cause un covering...

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