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PILOT`S OPERATING HANDÉOOK

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1. 5 PRESS FEET AEH HH um PEE pt ttt tt ei 5 10 15 20 25 30 GLIDE RANGE NAUTICAL MILES SEA LEVEL Example f ise pressure altitude 8000 ft ain pressure altitude 1500 ft Gude Range 13 miles minus 2 5 miles 10 5 nautical miles GLIDE RANGE Figure 5 3 ISSUED JULY 12 1977 REPORT 790 REVISED MAY 23 1980 5 31 5 RFORMANCE PIPER FT CORPORATION PA 28 181 ARCHER II NNNM ae PA 28 181 Hi 09 U3AD 334 190 SNIONYI c e gt 2 0 6 LA LA v Lec REC ES LAU Reefs WIND KNOTS 61 04 eT 1411 GROSS WEIGHT LBS MAXIMUM BRAKING PAVED LEVEL DRY RUNWAY 66 KIAS APPROACH SPEED FULL STALL TOUCH DOWN NM LLLLLLLLLLLAN VA LANDING PERFORMANCE Figure 5 3
2. ty ERES Lif Lis 4 arza GROSS WEIGHT LBS WIND KNOTS 40 10 0 20 OUTSIDE AIR TEMP C Example Departure airport pressure altitude 2000 ft Temperature 70 F Gross weight 2400 165 Wind 8 knots headwind Takeoff distance 1860 TAKEOFF DISTANCE OVER 50 FT BARRIER FEET 8 8 NOILVUOdHOD LIVE PIPER AIRCRAFT CORE ATION SECTION 5 PA 28 181 CHEROKEE ARCHER II PERFORMANCE 1333 1104 33033v1 way ZA pr AP AU 227 FT 000 0 0 0 1 WIND KNOTS UND ROLL SET RELEA WEIGHT POUNDS HE en AX 7L 17 HH AY HH 113 era IE t i THEE KL To Departure airport pressure altitude 2000 ft Temperature 70 Takeoff ground roll 1100 ft FLAPS UP TAKEORF GRO H H FULL THROTTLE BEFORE BRAKE Gross weight 2400 155 Wind 8 knots headwind OUTSIDE AIR TEMP C OUTSIDE AIR TEMP F 20 40 FLAPS UP TAKEOFF GROUND ROLL Figure 5 9 ISSUED JUNE 18 1976 REPORT V
3. 4 5 co 4 6 MASSAND BALANCE areas 5 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS v 5 8 AIRPLANE HANDLING CARE AND MAINTENANCE 8 AFM M12 Rev 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M12 GI 106A 1 GENERAL This Supplement supplies the information necessary for the efficient operation of the airplane when the CDI 106A is installed The information contained within this Supplement is to be used in conjunction with the complete Manual This Supplement is a permanent part of this Manual and must remain in this Manual as long as the CDI GI 106A is installed 2 OPERATING LIMITATIONS No change 3 EMERGENCY PROCEDURES No change NORMAL OPERATING PROCEDURES No change 48 ABNORMAL OPERATING PROCEDURES No change 5 PERFORMANCE No change 6 MASS AND BALANCE Upon removal or installation of the CDI the change of empty mass and AFM M12 Rev 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M12 GI 106A corresponding center of gravity of the airplane must be recorded according to Chapter 6 of the Airplane Flight Manual 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS SEE AIRPLANE AND ITS SYSTEMS 7 14 AVIONICS GENERAL The 106A Course Deviation Indicator is designed to operate with VHF and GPS navigational equipment to provide VOR Localizer LOC GPS and Glideslope GS information The
4. 10 Transceiver Cert Basis TC 2A13 Narco Comm 11A VHF Transceiver a Single b Dual Cert Basis TC 2A13 Narco Comm 11B VHF Transceiver a Single b Dual Narco Comm 111 VHF Transceiver a Single b Dual Cert Basis TSO C37b C38b Narco Comm 111B VHF Transceiver a Single b Dual Cert Basis TSO C375 C38b Narco Comm 120 VHF Transceiver a Single b Dual Cert Basis TSO C37b C38b Narco Nav 10 VHF Receiver Cert Basis TC 2A13 Narco Nav 11 VHF Receiver a Single b Dual Cert Basis TC 2A13 Narco Nav 12 VHF Receiver Cert Basis TC 2A13 ISSUED JUNE 18 1976 REVISED JULY 12 1977 Mark if Instl co Ov Weight Pounds 3 9 aw 3 4 SECTION WEIGHT AND BALANC Arm In Momen Aft Datum Lb In 57 4 224 57 4 207 57 4 408 57 4 224 57 4 448 57 4 172 57 4 344 57 4 224 57 4 448 56 9 273 57 4 494 58 6 111 58 6 164 58 6 328 58 6 199 REPORT 7 6 TION 6 PIPER AIRCRAFT CORPORATION IGHT AND 28 181 CHEROKEE ARCHER m Radio Equipment Optional Equipment cont m Mark if Weight Arm In Moment Instl Pounds Aft Datum Lb In 1 Narco 14 Receiver Cert Basis 2A13 a 25 57 4 144 3 Narco 111 Cert Basis TSO C36c RA 2 5 58 6 147 5 Narco Nav 112 R
5. PRESSURE 4 5 5 6 7 ENDURANCE HOURS E ole se pressure altitude 2000 ft Power setting 65 Endurance with reserve 5 5 hrs Endurance no reserve 6 1 hrs ENDURANCE Figure 5 27 ISSUED JULY 12 1977 REPORT 790 REVISED MAY 23 1980 5 29 CTION 5 PIPER RAFT CORPORATION RFORMANCE 28 18 _ HEROKEE ARCHER II PA 28 181 2550 LBS GROSS W Tj Al LIA TLLA Fa H H in Destination LA 4 i L1 5A CCC F 20 0 20 40 60 80 100 0 5 1 15 20 25 30 35 40 TIME DISTANCE AND FUEL TO DESCEND 45 50 55 ttt Ju C 0 0 0 0 10 20 30 OUTSIDE AIR TEMP ample Cruise pressure altitude 6000 ft Cruise OAT 55 F Destination airport pressure altitude 2300 ft Destination airport temperature 70 F uel to descend 2 0 gal minus gal 1 0 gal Time to descend 16 min minus 7 5 min 8 5 min Distance to descend 35 miles minus 14 5 miles 20 5 nautical miles TIME DISTANCE AND FUEL TO DESCEND Figure 5 29 ISSUED JULY 12 1977 EPORT VB 790 REVISED MAY 23 1980 30 PIPER AIRCRAFT CORPO ION SECTION 5 28 181 CHEROKEE ARCHER H PERFORMANCE AE e 81
6. 7 PIPER AIRCRAFT CORPO _ SECTION 3 PA 28 181 CHEROKEE ARCHER EMERGENCY PROCEDURES 3 EMERGENCY PROCEDURES 3 1 GENERAL The recommended procedures for coping with various types of emergencies and critical situations are pr ded by this section All of required FAA regulations emergency procedures and those necessary for eration of the airplane as determined by the operating and design features of the airplane are presented Emergency procedures associated with those optional systems and equipment which require handbook supplements are provi in Section 9 Supplements The first portion of this section consists of an abbreviated emergency check list which supplies an action sequence for critical situations with little emphasis on the operation of systems The remainder of the section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures These procedures are suggested as the best course of action for coping with the particular condition described but are not a substitute for sound judgment and common sense Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should emergency arise Most basic emergency procedures such as power off landings are a normal part of pilot training Although these emergencies
7. RANGE ARE N RANGE WITH 0 RESERVE RANGE WITH 45 RESERYE AT 55 7 1 LLL LLLA WER 1 THEY EA LLLA COCCI HTC eee Poe eh 0 20 40 60 80 100 F 400 500 600 500 500 700 20 0 0 10 20 30 40 C RANGE NAUTICAL MILES OUTSIDE AIR TEMP xample Cruise pressure altitude 5500 ft Cruise OAT 35 Power setting 75 Range with reserve 505 nautical miles Range no reserve 560 nautical miles BEST POWER MIXTURE RANGE SERIAL NOS 28 7890001 AND UP Figure 5 24 REPORT 790 ISSUED JUNE 18 1976 5 26 REVISED MAY 23 1980 PIPER AIRCRAFT RATION SECTION PA 28 181 CHEROKEE ARCHER II PERFORMANC e GN MIXTURE LEANED TO PEAK FAIRINGS INSTALLED 48 GAL USABLE FUEL 2550 LBS GR WT WIND RANGE INCLUDES CLIMB amp DESCENT DISTANCE J nM 1 BH SH PEE LI TIS LI ELT LIT IT LLLA TZ d REECE POAC TVA EEE EE MIT III 071 20 20 40 60 80 100 F 700 500 700 RA
8. Weight Pounds 15 525 4 6 5 6 Arm In Moment Aft Datum Lb In 94 5 208 132 1 391 140 3 224 109 5 22 101 9 285 71 0 327 57 9 324 ISSUED JUNE 18 1976 REVISED JULY 3 1978 PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER II SECTION 6 WEIGHT AND BALANCE 11 n Miscellaneous Optional Equipment cont Item No Item TOTAL OPTIONAL EQUIPMENT EXTERIOR FINISH Base Color Trim Color Accent Color ISSUED JUNE 18 1976 Weight Arm In Moment Pounds Aft Datum Lb In Registration No Color Type Finish REPORT VB 790 6 51 PIPER AIRCRAFT CORPORATION 6 SIGHT AND BALAN PA 28 181 CHEROKEE ARCHER II o THIS PAGE INTENTIONALLY LEFT BLANK EPORT VB 790 ISSUED JUNE 18 1976 52 SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEM SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS i 5 SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS Paragraph Page 7 1 eus 7 1 7 3 BEINE e ern G4 TH 7 1 7 5 ANC PrODSlef re cue SOTA HS nee a 7 1 Eon mio Xon 7 3 axe
9. THIS INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 5 2 PIPER AIRCRAFT SECTION 5 PA 28 181 CHEROKEE ARCHER II PERFORMANCE 5 5 FLIGHT PLANNING EXAMPLE a Aircraft Loading The first step in planning our flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 Weight and Balance of this handbook The basic empty weight for the airplane as delivered from the factory has been entered in Figure 6 5 any alterations to the airplane have been made effecting weight and balance reference to the aircraft logbook and Weight and Balance Record Figure 6 7 should be made to determine the current basic empty weight of the airplane Make use of the Weight and Balance Loading 6 1 1 and the C G Range and Weight graph Figure 6 15 to determine the total weight of the airplane and the center of gravity position After proper utilization of the information provided we have found the following weights for consideration in our flight planning example The landing weight cannot be determined until the weight of the fuel to be used has been established refer to item 8 1 1 Basic Empty Weight 1400 Ibs 2 Occupants 2 x 170 Ibs 340 155 3 Baggage and Cargo 360 155 4 Fuel 6 15 821 x 50 300 155 5 Takeoff Weight 2400 Ibs 6 Landing Weight a 5 minus g 1 2400 Ibs minus
10. SUBTRACT 8 KTS IF REMOVED 714 EN ANA d YSZ Z WW s amp LIPS 4 E u I eRe DEENS EE VU LL Vul 44 TA FEFTLEHLEUITLITILULTCELELCEL ZOZI ALY VI Z x IL 131 3 1 1 BEREIT I ZI VIA TANZ a 6 5 20 0 20 40 60 80 100 F 80 100 110 120 130 140 20 0 20 40 C TRUE AIRSPEED KTS QUTSIDE AIR TEMP Example Cruise pressure altitude 6000 ft Cruise OAT 55 F Powersetting 65 True airspeed 116 knots SPEED POWER ECONOMY CRUISE SERIAL NOS 28 7890001 AND UP Figure 5 22 ISSUED JUNE 18 1976 REPORT VB 790 REVISED JULY 12 1977 PIPER AIRCRAFT CORPO ION SECTION 5 PA 28 181 CHEROKEE ARCHER II PERFORMANCE 28 181 BEST POWER RANGE RE LEANED 100 F RICH OF PEAK EGT WHEEL FAIRINGS INSTALLED 48 GAL USABLE FUEL 2550 LBS ZERO WIND 4s MIN RESERVE ELEZ RANGE IN
11. Engine Power Loss During Engine Power Loss In Flight DUM E F Loss Of Oil Pressure 11 14 WASP ee ee oe Loss OF Fuel Pressure RN MINE HEN HighOil roti MD Ee Alternator Failure RN 2 Spin E i 8 T MEE Engine Roughness insertis iaso 5 2 5 Amplified Emergency Procedures General v s Der ERE 2 2 7 Engine 2 39 Engine Power Loss During 2 2 EEE EEE 2 3 15 2 3 17 Ra 3 3 19 VOOR 3 321 pris incpa gates 3 323 BSR FAROE TE nce ie nn 3 3 25 RECOVERY 3 3 328 Loss amorem reme ti UTER CTS eC TEES I MTS LS TE 3 3 29 Engine 3
12. DA ae pco aie 2 3 243 Gravity ous Suae eo ER ers 2 4 2 15 Mane ver Limits 3 i aa EUR T EDS 2 4 217 Factors Sue 2 4 2 19 Of Operations lt gt qx aue pei tog TR Wad 2 5 2 21 A Fuel Limitations a caga err Eu deu 2 5 2 29 Placards shoe eu Gdn eae gees ae oe ee 2 7 790 24 PIPER AIRCRAFT CORP ATION SECTION 2 28 151 CHEROKEE A LIMITATIONS eee SECTION 2 LIMITATIONS 2 1 GENERAL This section provides the FAA Approved operating limitations instrument markings color coding and basic placards necessary for the operation of the airplane and its systems This airplane must be operated as a normal or utility category airplane in compliance with the ating 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 which require handbook supplements can be found in Section 9 Supplements 2 3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed Yne Do not exceed this speed in any operation 154 148 Maximum Structural Cruising Speed Do not exceed this s
13. hec ore du EAM Cadete S VITE 5 12 5 5 Flaps Up Takeoff Performance nn 5 13 5 7 25 Flaps Takeoff Performance naaa 5 14 5 9 Flaps Up Takeoff Ground 5 15 25 Flaps Takeoff Ground 5 16 pita 5 17 515 Time Distance and Fuel to Climb aaua e 5 18 5 17 Engine Performance Serial Nos 28 7790001 fhrough 7790507 cues oni 5 19 5 18 Engine Performance Serial Nos 28 7890001 and UD ener 5 20 5 19 Speed Power Performance Cruise Serial Nos 28 7790001 through 7790607 5 21 5 20 Speed Power Performance Cruise Serial Nos 28 7890001 and BO mappe ee 5 22 5 21 Speed Power Economy Cruise Serial Nos 28 7790001 through 7190807 aee 5 23 5 22 Speed Power Economy Cruise Serial Nos 28 7890001 and MD qu asa cx uta ACE 5 24 5 23 Best Power Mixture Range Serial Nos 28 7790001 through 7790607 5 25 5 24 Best Power Mixture Range Serial Nos 28 7890001 VD no quovis ere 5 26 5 25 Best Economy Mixture Range Serial Nos 28 7790001 through 7790607 5 27 5 26 Best Economy Mixture Range Serial Nos 28 7890001 and NU cw 5 28 521 ere mas 5 29 5 29 Time Distance and Fu
14. sets navigation grid units to decimal minutes NOTE In some areas outside the United States datums other than WGS 84 or NAD 83 may be used If the GNS 430 is authorized for use by the appropriate Airworthiness authority the required geodetic datum must be set in the GNS 430 prior to its use for navigation SECTION HL EMERGENCY PROCEDURES ABNORMAL PROCEDURES 1 If GARMIN GNS 430 navigation information is available or invalid utilize remaining operational navigation equipment as required RAIM POSITION WARNING message is displayed the system will flag and no longer provide GPS based navigational guidance The crew should Tevert to the GNS 430 VOR ILS receiver or an altemale means of navigation other than the GNS 430 s GPS Receiver lf RAIM IS NOT AVAILABLE message is displayed in the enroute terminal or initial approach phase of flight continue to navigate using the GPS equipment or revert alternate means of navigation other than the GNS 430 5 GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the GNS 430 s VOR ILS receiver or another IFR approved navigation system PIPER PA32 FAA APPROVED 190 00 140 03 Rev DATE 11 21 02 Page 7 of 10 GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION
15. RR __ 4 13 4 29 Approach and Landing 112200 4 14 4 31 Stopping Engine 1 tte 4 5 434 um 4 15 4 45 e reper nde ee bel DR s a i PARA EN M 4 15 4 33 Turbulent Air Operation 4 4 16 4 39 Weight and Balance 1 4 16 REPORT VB 790 4 i PIPER AIRCRAFT CORPO SECTION 4 PA 28 181 CHEROKEE ARCHER II NORMAL PROCEDURES _ SECTION 4 NORMAL PROCEDURES 4 1 GENERAL This section clearly describes the recommended procedures for the conduct of normal operations for the Cherokee Archer II of the required FAA regulations procedures and those necessary for the safe of the airplane as determined by the operating and design features of the airplane are presented Normal procedures associated with those optional systems and equipment which require handbook supplements are provided by Section 9 Supplements These procedures are provided to present a source of reference and review and to supply information on procedures which are not the same for all aircraft Pilots should familiarize themselves with the procedures given in
16. 100 2000 2200 2400 OUTSIDE AIR TEMP ENGINE SPEED R P M 20 10 0 10 20 30 OUTSIDE AIR TEMP C Example Cruise pressure altitude 5500 ft Cruise OAT 4 Percent power 6595 Engine RPM 2440 RPM ENGINE PERFORMANCE SERIAL NOS 28 7790001 THROUGH 7790607 Figure 5 17 ISSUED JUNE 18 1976 REPORT VB 790 REVISED JULY 12 1977 5 19 SECTION 5 PIPER AL iAFT CORPORATION 28 181 CHEROKEE PERFORMANCE Hr ENGINE PERFORMANCE HHHH PA sr ae INSTRUCTINS gt LEANED FUEL FLOW GALLONS PER HOUR POWER BEST ECOKONY 4 4 4 BEDANE 11110 2000 2200 2400 2500 ENGINE SPEED RPM 20 0 20 40 C QUTSIDE AIR TEMP Example Cruise pressure altitude 5500 ft Cruise OAT 40 F Percent power 65 Engine RPM 2440 RPM ENGINE PERFORMANCE SERIAL NOS 28 7890001 AND UP Figure 5 18 REPORT VB 790 ISSUED JUNE 18 1976 5 20 REVISED JULY 12 1977 PIPER AIRCRAFT ON SECTION 5 PA 28 181 CHEROKEE ARGacR PERFORMANCE PA 28 181 SPEED POWER PERFORMANCE CRUISE BEST POWER MIXTURE Z 2550 LBS GROSS WEIGHT MIXTURE FULL RICH ABOVE 75 LEANED 100 F RICH OF PEAK BELOW 75 POWER WHEEL FAIRINGS LLULTINTTTT Lt VT TT SY B
17. PILOT S OPERATING HANDBOOK PIPER CHEROKEE ARCHER II FAA APPROVED IN NORMAL AND UTILITY PA 28 181 CATEGORIES BASED ON 3 AND FAR PART 21 REPORT VB 790 SUBPART J THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE OT BY CAR 3 AND FAR PART 21 SUBPART J EDU ond Ev one CONSTITUTES THE APPROVED AIRPLANE WARD EVANS FLIGHT MANUAL AND MUST BE CARRIED IN THE D 0 A NO 50 1 AIRPLANE AT ALL TIMES xS PIPER AIRCRAFT CORPORATION gt VERO BEACH FLORIDA 28 7890244 AIRPLANE SERIAL No _28 7890244 is gt QE DKT DAMM AIRPLANE REGISTRATION UO DATE OF APPROVAL JUNE 18 1976 HANDBOOK PART NO 761 624 WARNING 4 EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL TO APPLICABLE AIRCRAFT THIS MANUAL REVISED AS INDICATED BELOW OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE WHEN OFFICIALLY APPROVED SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED MODEL 28 181 CHEROKEE ARCHER lt PILOT S OPERATING HANDBOOK REVISION 20330 Es PIPER AIRCRAFT CORPORATION Ad gt 43 APPROVAL SIGNATURE AND STAMP x Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation Issued June 18 1976 REPORT VB 790 il ll The aircraft seria number el
18. TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page No Denen 10 1 203 Operating Tips eI DAMEN ERE aides a Is 10 1 REPORT 790 104 A 2 2 o P une TET i 254 y Rp gt AC m 2 Est X Ve un ye IP ex 2 452 SECTION 10 PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER OPERATING TIPS SECTION 10 OPERATING TIPS 10 1 GENERAL This section provides operating tips of particular value in the operation of the Cherokee Archer 0 3 OPERATING TIPS b c d e f h i Learn to trim for takeoff so that only a very light back pressure on the control wheel is required 19 lift the airplane off the ground The best speed for takeoff is about 53 KIAS under normal conditions Trying to pull the airplane off the ground at too low an airspeed decreases the controllability of the airplane in the event of engine failure Flaps may be lowered at airspeeds up to 102 KIAS To reduce flap operating loads it is desirable to have the airplane at a slower speed before extending the flaps The flap step will not support weight if the flaps are in any extend
19. 0 2200 Imperial gal millimeters mm 0 03937 in 1 05669 qt millimeters of 0 03937 in H liters per hectare 13 69 fl oz acre mercury at 0 I ha 0 107 gal acre mm Hg liters per second 2 12 cu ft min nautical miles 6080 ft NM 1 1516 statute mi 1852 meters m 39 37 in 1 852 3 280840 ft 1 0936 yd ounces avd 28 35 9 g 0 198838 a oz avdp 16 dr avdp 6 214 x IO 5 3996 x 10 NM ounces fluid 8 dr fl 07 29 57 3 meter kilogram 7 23301 ft lb 1 805 m m kg 86 798 in Ib 0 0296 1 0 0078 U S gal ISSUED JUNE 18 1976 REPORT VB 790 REVISED FEBRUARY 28 1979 1 13 SECTION 1 GENERAL MULTIPLY yunces fluid per acre oz pounds 10 pounds per Ib acre pounds per cubic foot Ib cu ft pounds per cubic inch Ib cu in pounds per square foot 1b sq ft pounds per square inch psi or 1b sq in quart U S qt radians radians per second radians sec revolutions rev revolutions per minute rpm or rev min revolutions per second rev sec REPORT VB 790 1 14 BY 0 073 0 453592 453 6 8 108 x 10 1 121 16 02 1728 27 68 0 1414 4 88243 4 725 x 10 5 1715 2 036 0 06804 0 0689476 703 1 0 94635 57 749 57 30 0 1592 57 30 0 1592 9 549 6 283 0 1047 6 283 TO OBTAIN l ha kg 5 siug kg ha kg m Ib cu ft g cm in Hg k
20. 106A is designed to accept signals from a remote mounted VOR converter or GPS receiver Additionally it will accept signals from a glideslope receiver which will drive the Glideslope Deviation Bar along with an Glideslope warning flag The unit incorporates NAV GPS and VLOC VOR LOC as displayed on the Garmin GNS 430 annunciation with photocell dimming When GPS is selected for display the GI 106A receives inputs from the GPS receiver to provide a visual presentation to the pilot All information presented on the navigation indicator is generated from this external receiver AFM M12 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M12 GI 106A Glideslope Channel the VOR ILS receiver to the desired VOR frequency and positively identify the station by listening to received audio Determine the left right VOR LOC warning flag is out of view Flying inbound to a VOR station is accomplished by first rotating the OBS knob to center the deviation indicator and determining the TO FROM indicator is in the TO condition Read the To bearing under the top indicator index and maneuver the airplane to approximately fly the magnetic course To the station When the airplane is on course the vertical pointer will be centered If the airplane moves off the course the deviation bar will move away from the center position and flying in the direction of pointer deflection left or
21. 3 Remove oil and grease with a cloth moistened with kerosene CAUTION Do not use gasoline alcohol benzene carbon tetrachoride thinner acetone or window cleaning sprays REPORT VB 790 ISSUED JUNE 18 1976 8 14 PIPER AIRCRAFT CORPORATION 2 SECTION 8 28 181 CHEROKEE ARCHER II HANDLING SERVICING AND MAINTENANCE 4 After cleaning plastic surfaces apply a thin coat of hard polishing wax Rub lightly with a soft cloth Do not use a circular motion 5 A sever scratch or mar in plastic can be removed by rubbing out the scratch with jeweler s rouge Smooth both sides and apply wax e Cleaning Headliner Side Panels and Seats s 1 Clean headliner side panels and seats with a stiff bristle brush and vacuum where necessary 2 Soiled upholstery except leather may be cleaned with a good upholstery cleaner suitable for the material Carefully follow the manufacturer s instructions Avoid soaking or harsh rubbing CAUTION Solvent cleaners require adequate ventilation 3 Leather should be cleaned with saddle soap or a mild hand soap and water f Cleaning Carpets To clean carpets first remove loose dirt with a whisk broom or vacuum For soiled spots and stubbom stains use a noninflammable dry cleaning fluid Floor carpets may be removed and cleaned like any household carpet 8 29 COLD WEATHER OPERATION For cold weather operation a winterization plate is installed on the inlet opening of the oil co
22. 8 15 LANDING GEAR SERVICE The three landing gears use Cleveland Aircraft Products 6 00 x 6 four ply rating type tires and tubes Refer to paragraph 8 23 Wheels are removed by taking off the hub cap cotter pin axle nut and the two bolts holding the brake segment in place Mark tire and wheel for reinstallation then dismount by deflating the tire removing the three through bolts from the wheel and separating the wheel halves Landing gear oleos on the Cherokee Archer 1I should be serviced according to the instructions on the units The main oleos should be extended under normal static load until 4 50 25 inches of oleo piston tube is exposed and the nose gear should show 3 25 25 inches Should the strut exposure be below that required it should be determined whether air or oil is required by first raising the airplane on jacks Depress the valve core to allow air to escape from the strut housing chamber Remove the filler plug and slowly raise the strut to full compression If the strut has sufficient fluid it will be visible up to the bottom of the fil plug hole and will then require only proper inflation Should fluid be below the bottom of the filler plug hole should be added Replace the plug with valve core removed attach a clear plastic hose to the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid Fully compress and extend the strut several times thus drawing fluid from t
23. 8 8 8 13 Brake Service sw v oe 8 8 8 15 TY P ees 8 10 8 17 Propeller Service 45 ee rA DR Su 8 11 8 19 Dil Requirements b ERE e n Es 8 11 8 21 Fuel System ne an HERA GEES 8 11 8 23 Tire Inflation aw wu HER 8 13 8 25 Battery Service z 99 94 VJ ms ay exe eur ats Yi BID wa Wm ERES 8 13 oU AN MAC 8 13 8 29 Cold Weather Operation esses en Bis Wis Be mn ane sow 8 15 790 8 1 PIPER AIRCRAFT CORPORATION SECTION 8 PA 28 181 CHEROKEE ARCHERII HANDLING SERVICING AND MAINTENANCE LS nn SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE 8 1 GENERAL This section provides general guidelines relating to the handling servicing and maintenance of the Archer For complete maintenance instructions refer 10 the PA 28 Service Manual Every owner should stay in close contact with an authorized Piper Service Center or Pipers Customer services Department to obtain the latest informztion to their airplane and to avail themselves of Piper Aircraft s support systems Piper Air
24. FAN switch with 4 positions OFF LOW or HIGH CAUTION When cabin heat is operated heat duct surface becomes hot This could result in burns if arms or legs are placed too close to heat duct outlets or surface 7 25 CABIN FEATURES For ease of entry and exit and pilot passenger comfort the front seats are adjustable fore and aft The Tear seats may be removed to provide room for bulky items Rear seat installations incorporate leg retainers with latching mechanisms which must be released before the rear seats can be removed Releasing the retainers is accomplished on earlier models by turning the latching mechanisms 90 with a coin or screwdriver Releasing the retainers is accomplished on later models by depressing the plunger behind each rear leg Armrests are also provided for the front seats seats are available with optional headrests and optional vertical adjustment may be added to the front seats The cabin interior includes a pilot storm window two sun visors ash trays two map pockets and pockets on the backs of each front seat single strap shoulder harness controlled by an inertia reel is standard equipment for the front seats is offered as an option for the rear seats The shoulder strap is routed over the shoulder adjacent to the windows and attached to the lap belt in the general area of the person s inboard hip check of the inertia ree mechanism is made by pulling sharply on t
25. H 4 7 29 4 WALK AROUND Figure 4 1 4 5 NORMAL PROCEDURES CHECK LIST 5 ovo ae EX remove cover PREFLIGHT holes clear i cree amp ocn es clean Control wheel u especie ix release belts Propeller and check Master switch ae an ve ON check for leaks Fuel quantity gauges been check hr RU ta check level Master switch uet ea OFF Dipstick tede et properly seated lgnitiong E OR OFF Gor s cie sepe ride est secure ascribi Ree check for damage Inspection covers secure Control surfaces check for interference Nose wheel tire erar check free of ice snow frost Nose pear ciues ratione Qn proper Hinges nase check for interference inflation 3 25 in WINES uae ug free of ice snow frost clear Stall warnings ccc check Alternator belt check tension Navigation lights a rre rea check Tow bar and control locks 510 tos check supply aaa stowed properly visually secure caps secure Fuel tank 5 drain
26. ISSUED JUNE 18 1976 PORT VB 790 REVISED MAY 23 1980 PIPER AIRCRAFT CORPO SECTION 5 28 181 CHEROKEE ARCHER II PERFORMANCE d Descent The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance Utilizing the cruise pressure altitude and OAT we determine the basic time distance and fuel for descent Figure 5 29 These figures must be adjusted for the field pressure altitude and temperature at the destination airport To find the necessary adjustment values use the existing pressure altitude and temperature conditions at the destination airport as variables to find the time distance and fuel values from the graph Figure 5 29 Now subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true time distance and fuel values needed for the flight plan 4 The values obtained by proper utilization of the graphs for the descent segment of our example are shown below 1 Time to Descend 16 min minus 7 5 min 8 5 min 2 Distance to Descend 35 minus 14 5 nautica miles 20 5 nautical miles 3 Fuel to Descend 2 0 gal minus 1 gal 1 0 gal e Cruise Using the total distance to be traveled during the flight subtract the previously calculated distance to climb and distance to descend to establish the total cruise distance Refer to the appropr
27. Mixt re erre s m hates As required POWELL rcr Verify with throttle every 30 seconds REPORT VB 790 4 5 PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER II 4 NORMAL PROCEDURES APPROACH AND LANDING Fuel selector 20 osoon soeren proper tank Seat backs ntm erect Belts harness n nnn fasten adjust Electric fuel pump 59 ON Mixture set 1 ass ae set 102 KIAS max conditioner OFF to 75 KIAS Final approach speed flaps 40 66 KIAS STOPPING ENGINE retract Electric fuelpump OFF Air conditioner Radios RR OFF Throttle aos ere ne full aft Mixt re 24 xxx RR idle cut off Mametos i xac ho OFF Masterswitch uoo xen OFF 5 PARKING Parking brake uu ade ande set Control wheel secured with belts Senna se full up Wheel chocks in place downs p oes Ee Say a Reo secure REPORT 790 4 6 ISSUED JUNE 18 1976 REVISED MARCH 30 1984 stersen Aviation Inc Deutscher Aero Club e V 1 inden NE USA lt i Hermann Blenkstr 28 38108 Braunschweig Am Instrumentenbrett im direkten Slickfeld des Piloten ist folgendes Hinweisschild
28. NO ACROBATIC MANEUVERS ARE APPROVED FOR NORMAL CATEGORY OPERATIONS SPINS ARE PROHIBITED FOR NORMAL AND UTILITY CATEGORY In full view of the pilot one of the will be installed Fuel on proper tank Electric fuel pump on Engine gauges checked Flaps set Carb heat off Fuel on proper tank Electric fuel pump on Engine gauges checked set heat off Fuel on proper tank Mixture rich Electric fuel pump on The AIR COND OFF item in conditioned aircraft only ISSUED JUNE 18 1976 REVISED JULY 3 1978 following takeoff checklists and the following landing check list TAKEOFF CHECK LIST Fasten belts harness Trim tab set Controls free Door latched Air Conditioner off Mixture set Seat backs erect TAKEOFF CHECK LIST Fasten belts harness Trim tab set Controls free Door latched Air conditioner off Mixture set Primer locked Seat backs erect LANDING CHECK LIST Flaps set 102 KIAS max Fasten belts harness Seat back erect Conditioner off the above takeoff and landing check lists is mandatory for air REPORT VB 790 2 7 SECTION 2 PIPER CORPORATION LIMITATIONS PA 28 181 HEROKEE ARCHER U In full view of the pilot the area of the air conditioner control panel when the air conditioner is installed WARNING AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE Adjacent to upper door la
29. PA 28 181 TIME SISTANCE LT LELLELLLLLLL AND FUEL TO CLIMB 76 KIAS AND FULL THROTTLE 1 19550 185 GROSS WEIGHT EL IL Ee derer MIXTURE TH LEANED 100 F RICH OF ir Zn CHART maine FUEL ALLOWANCE Ht tf fat top START TAXI AND TAKEOFF a 20 0 20 40 60 80 10 0 5 10 15 20 25 30 35 40 45 4 55 60 OUTSIDE AIR TEMP F TIME DISTANCE AND FUEL TO CLIMB 20 10 0 10 20 OUTSIDE AIR xample Departure airport pressure altitude 2000 ft Departure airport temperature 70 F Cruise pressure altitude 6000 ft Cruise OAT 55 F Time to climb 11 5 min minus 3 min 8 5 min Distance to climb 16 miles minus 4 5 miles 11 5 nautical miles Fuel to climb 2 gal minus gal gal TIME DISTANCE AND FUEL TO CLIMB Figure 5 15 ISSUED JUNE 18 1976 REPORT VB 790 REVISED MAY 23 1980 5 18 PIPER AIRCRAFT CORPO SECTION 5 PA 28 181 CHEROKEE ARCHER PERFORMANCE PA 28 181 B RR ENGINE AE A A AZT PERFORMANCE BEST POWER MIXTURE LEANED 9 100 F RICH OF PEAK EST H LLLITFE CEE te Ar Hus LT 20 0 20 40 50
30. REPORT VB 790 1 11 1 GENERAL MULTIPLY BY feet per second 0 6818 ft sec 1 097 30 48 0 5921 foot pounds ft Ib 0 138255 3 24 10 foot pounds per 3 030 x 10 minute ft Ib min foot pounds per 1 818 x 10 second ft Ib sec gallons Imperial 277 4 Imperial gal 1 201 4 546 gallons U S dry 268 8 U S gal dry 1 556 x 107 1 164 4 405 gallons U S liquid 231 U S gal 0 1337 4 95 x 10 3785 4 3 785 x 10 3 785 0 83268 128 allons per acre 9 353 gal acre zrams g 0 001 0 3527 5 2 205 x 10 rams centimeter 0 1 g cm 6 721 x 10 5 601 x 10 rams per cubic 1000 centimeter g cm 0 03613 62 43 REPORT VB 790 12 km hr cm sec kts m kg kg cal hp hp cu in U S gal 1 cu in cu ft U S gal cu in cu ft cu yd cm m 3 1 Imperial gal fl oz l ha kg oz avdp Ib kg m Ib ft 1b in kg m Ib cu in Ib cu ft PIPER RAFT CORPORATION 28 18 JEROKEE ARCHER II MULTIPLY BY hectares ha 2 471 107639 10000 horsepower hp 33000 550 76 04 1 014 horsepower metric 75 0 9863 inches 25 40 2 540 0 0254 0 08333 0 027777 inches of mercury 0 033421 at 0 C Hg 0 4912 70 73 345 3 2 540 25 40 inch pounds in Ib 0 01 1521 kilograms kg 2 204622 35 27 1000 kilogram calories 3 9683 kgcal 3087 426 9 kilograms per cubic
31. TC 2A13 Landing Light G E Model 4509 Cert Basis TC 2A13 Navigation Lights Wing 2 Grimes Model A1285 Red and Green Cert Basis TC 2A13 Navigation Light Rear 1 Grimes Model 2064 White Cert Basis TC 2A13 Rotating Beacon Cert Basis TC 2413 Anti Collision Lights Wing Tip Whelen Cert Basis STC SA800EA Heated Pitot Head Piper Dwg 69041 7 Cert Basis TC 2A13 Piper Pitch Trim Piper Dwg 69378 3 Cert Basis TC 2A13 Battery 12V 35 R35 Wt 27 2 lbs Cert Basis TC 2A13 ISSUED JUNE 18 1976 REVISED JULY 3 1978 Mark if Instl X Weight Pounds 0 3 0 1 0 3 0 4 5 7 4 7 53 WEIGHT SECTION 6 AND BALANCE Arm In Moment Aft Datum Lb In 62 8 19 99 0 10 99 0 30 13 1 7 106 6 43 281 0 56 263 4 395 157 9 900 100 0 40 145 6 684 168 0 890 REPORT VB 790 6 35 CTION 6 IGHT AND BALANC G Electrical Equipment Optional Equipment cont o Item 01 Auxiliary Power Receptacle Piper Dwg 68815 Cert Basis 2413 23 External Power Cable Piper Dwg 62355 Cert Basis TC 2A13 25 Lighter 200462 12 Volt Universal Cert Basis TC 2A13 ORT 790 Mark if Instl mo dm x PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER _ lt Weight Pounds 2 7 4 6 Arm In Aft Datum 178 5 142 8 62 9 Moment Lb In
32. TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER If 15 NOT AVAILABLE message Is displayed while on the final approach segment GPS based navigation will continue for up to 5 minutes with approach CDI sensitivity 0 3 nautical mile Afler 5 minutes the system will flag and no longer provide course guidance with approach sensitivity Missed approach course guidance may still be available with nautical mile CDI sensitivity by executing the missed approach 5 In in flight emergency depressing and holding the Comm transfer button for 2 seconds will select the emergency frequency of 121 500 MHz into the Active frequency window SECTION IV NORMAL PROCEDURES 1 DETAILED OPERATING PROCEDURES Normal operating procedures are described in the GARMIN GNS 430 Pilot s Guide P N 190 00140 00 Rev A dated October 1998 or later appropriate revision 2 PILOTS DISPLAY The GNS 430 System data will appear on the Pllot s HSI The source of data is either GPS or VLOC as annunciated on the display above the CDI key PIPER PA32 190 001 40 03 Rev FAA APPROVED Page 8 of 10 DATE 11 21 02 GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEM ENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER 3 AUTOPILOT FLIGHT DIRECTOR OPERATION DIREC LOR OPERATION Coupling of the GNS 430 System steering information 10 the autop
33. The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time The following flight time is required for our flight planning example 1 Total Flight Time c 3 plus 400 plus e 6 14 hrs plus 14 hrs plus 2 56 hrs 2 84 hrs g Total Fuel Required Determine the total fuel required by adding the fuel to climb the fuel to descend and cruise fuel When the total fuel in gallons is determined multiply this value by 6 lb gau determine the total fuel weight used for the flight The total fuel calculations for our example flight plan are shown below 1 Total Fuel Required 5 plus d 3 plus 7 1 gal plus 1 gal plus 19 5 gal 21 5 gal 21 5 gal multiplied by 6 Ib gal 129 155 REPORT VB 790 ISSUED JUNE 18 1976 5 6 REVISED MA Y 23 1980 PIPER AIRCRAFT CORP ATION SECTION 5 PA 28 181 CHEROKEE ARCHER II PERFORMANCE THIS INTENTIONALLY LEFT BLANK ISSUED JUNE 18 1976 REPORT VB 790 5 7 PIPER A RAFT CORPORATION ECTION 5 ERFORMANCE PA 28 181 CHEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK EPORT VB 790 ISSUED JUNE 18 1976 8 PIPER AIRCRAFT 5 28 181 CHEROKEE Ah ER PERFORMANCE 5 7 PERFORMANCE GRAPHS LIST OF FIGURES Figure Page No No 5 Airspeed System Calibration 5 11 5 3 SEAL STEEL
34. the inertia reel type shoulder harness is installed a pull test of its locking restraint feature should be performed Turn ON the electric fuel purnp and turn OFF the air conditioner The mixture should be set in the ful RICH position The airplane should be trimmed to an initial approach speed of about 75 KIAS with a final approach speed of 66 KIAS with flaps extended The flaps can be lowered at speeds up to 102 KIAS if desired The mixture control should be kept in full RICH position to insure maximum acceleration if it should be necessary to open the throttle again Carburetor heat should not be applied unless there is an indication of carburetor icing since the use of carburetor heat causes reduction in power which may be critical in case ofa go around Full throttle operation with carburetor heat on can cause detonation The amount of flap used during landings and the speed of the aircraft at contact with the runway should be varied according 10 the landing surface and conditions of wind and airplane loading It is generally good practice to contact the ground at the minimum possibie safe speed consistent with existing conditions Normally the best technique for short and slow landings is to use full and enough powerto maintr the desired airspeed and approach flight path Mixture should be full RICH fuel on the fullest tank a electric fuel pump ON Reduce the speed during the flareout and contact the ground clos
35. to cause OMNI indicator Needle to swing left and right slowly Observe that control wheel rotates in direction of needle movement 2 Disengage AP ON OFF Switch Reset Radio Coupler control to HDG IN FLIGHT a Trim airplane ball centered b Check air pressure vacuum to ascertain that the directional gyro and attitude gyro are receiving sufficient air c RollSection 1 To engage center ROLL knob push AP ON OFF switch to ON position To turn rotate console ROLL knob in desired direction Maximum angle of bank should not exceed 30 2 For heading mode set directional gyro with magnetic compass Push directional gyro knob in rotate bug to aircraft heading Push console heading rocker HDG switch to ON position To select a new aircraft heading push D G heading knob IN and rotate in desired direction of turn to the desired heading d Radio Coupling VOR ILS with Standard directional gyro Optional 1 For VOR Intercepts and Tracking Select the desired VOR course and set the HDG bug to the same heading Select OMNI mode on the coupler and HDG Mode on the autopilot console 2 ForILS Front Course Intercepts and Tracking Tune the localizer frequency and place the HDG bug on the inbound front course heading Select LOC NORM mode on the coupler and HDG mode on the autopilot console 3 ForLOC Back Course Intercepts and Tracking Tune the localizer frequency and place HDG bug on the i
36. 0 06243 meter kg m 0 001 kilograms 0 892 hectare kg ha kilograms per square 0 9678 centimeter kg cm 28 96 14 22 2048 OBTAIN sq ft m 2 ft lb min ft Ib sec m kg sec metric hp m kg sec hp mm cm In ft yd atn Ib sq in Ib sq ft kg m cm Hg mm Hg m kg 02 avdp BTU ft Ib m kg b cu ft b acre atm in Hg 1b sq in b sq ft ISSUED JUNE 18 1976 REVISED FEBRUARY 28 1979 PIPER AIRCRAFT CORPt SECTION 1 28 181 CHEROKEE ARCHER GENERAL MULTIPLY BY TO OBTAIN MULTIPLY BY TO OBTAIN kilograms square 2 896 x 103 in Hg meters per minute 0 06 km hr meter kg m 1 422 x 10 1b sq in m min 0 2048 1b sq ft meters per second 3 280840 ft sec kilometers km 1x10 cm m sec 196 8504 ft min 3280 8 ft 2 237 mph 0 6214 3 6 km hr 0 53996 NM microns 3 937 x 10 in kilometers per hour 0 9113 ft sec hr 58 68 ft min miles statute mi 5280 ft 0 53996 kt 1 6093 km 0 6214 mph 1609 3 m 0 27778 m sec 0 8684 NM 16 67 m min miles hou 44 704 knots kt 1 nautical mph moh 4 470 107 tog 1 689 ft sec 1 467 ft sec 1 1516 statute mph 88 ft min 1 852 km hr 1 6093 km hr 51 48 m sec 0 8684 kt liters 1 10 em miles per hour 2 151 ft sec sq i cu m Square m hr sq 0 03531 cu ft 33 814 fl oz millibars 2 953 10 in Hg 0 264172 U S gal
37. 11 21 02 Page 3 of 10 GARMIN International Inc 1200 151 Street Olathe KS 66062 USA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER SECTION T CENERAL 1 The GNS 430 System is a fully integrated panel mounted instrument which contains VHF Communications Transceiver a VOR ILS receiver and a Global Positioning System GPS Navigation computer The system consists of a GPS antenna GPS Receiver VOR LOC GS antenna VOR ILS receiver VHF COMM antenna and Communications Transceiver The primary function of the VHF Communication portion of the equipment is to facilitate communication with Air Traffic Control The primary function of the VOR ILS Receiver portion of the equipment is to receive and demodulate VOR Localizer and Glide Slope signals The primary function of the GPS portion of the system is to acquire signals from the GPS system satellites recover orbital data make range and Doppler measurements and process this information in real time to obtain the user s position velocity and time 2 Provided the GARMIN GNS 430 s GPS receiver is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications for VFR IFR enroute terminal and non precision instrument approach GPS Loran C VOR VOR DME TACAN NDB NDB DME RNAV operation within the U S Na
38. 129 lbs 2271 Ibs Our takeoff weight is below the maximum of 2550 155 and our weight and balance calculations have determined our C G position within the approved limits b Takeoff and Landing Now that we have determined our aircraft loading we must consider all aspects of our takeoff and landing All of the existing conditions at the departure and destination airport must be acquired evaluated and maintained throughout the flight Apply the departure airport conditions and takeoff weight to the appropriate Takeoff Performance graph Figure 5 5 or 5 7 to determine the length of runway necessary for the takeoff and or the barrier distance The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and when established the landing weight REPORT VB 790 ISSUED JUNE 18 1976 REVISED 23 1980 PIPER CORPORATION SECTION 5 PERFORMANCE PA 28 181 CHEROKEE ARCHER U E 4 The conditions and calculations for our example flight are listed below The takeoff and landing distances required for our example flight have fallen well below the available runway lengths Departure Destination Airport Airport 1 Pressure Altitude 2000 ft 2300 ft 2 Temperature 70 70 3 Wind Component 10 KTS 5KTS 4 Runway Length Available 7000 ft 4500 ft 950 ft 825 5 Runway Required
39. 2 button a second time AIRPLANE RADIOS amp NAVIGATION NOTE Audio level is controlled by the selected nav radio volume control Pressing NAV 1 NAV 2 DME ADF 16 or MKR 2 see MARKER BEACON RECEIVER selects that audio source A second button press deselects the audio source SPEAKER OUTPUT Pressing the SPKR button 12 selects the airplane radios over the cabin speaker The speaker output is muted when a COM microphone is keyed INTERCOM SYSTEM ICS Intercom volume and squelch VOX are adjusted using the following front panel knobs LEFT SMALL Unit on off power control and Pilot ICS volume 5 Full counter clockwise DETENT position OFF LEFT LARGE KNOB Pilot squelch level 6 Clockwise rotation increases the amount of mic audio required to break squelch Full counter clockwise is the hot mic position RIGHT SMALL KNOB IN position Copilot ICS 4 Diamond MAINTENANCE Doc No AFM M10 GMA 340 volume OUT position Passenger ICS volume T RIGHT LARGE KNOB Copilot and passenger squelch level 8 clockwise rotation increases the amount of mic audio required to break squelch Fully counter clockwise is the hot mic position Each microphone input has dedicated VOX circuit to ensure that only the active microphone s is are heard when Squelch is broken This represents a vast improvement over single gate systems and reduces the amount of background noise in the headp
40. 3 9 57 4 224 b Dual ERS 7 9 57 4 453 Cert Basis TSO 40 C36c Collins IND 350 VOR LOC Indicator a Single Zon 1 0 60 2 60 b Dual Py 2 0 60 2 120 Cert Basis TSO C40a C36c 5 Collins IND 351 VOR LOC GS Indicator gt C36c Me 1 3 60 2 78 7 Collins GLS 350 Glide Slope Receiver Cert Basis TSO C34c 2 0 181 8 364 PORT 790 JSSUED JUNE 18 1976 0 REVISED MAY 23 1980 PIPER AIRCRAFT CORPORATION SE WEIGHT AND PA 28 181 CHEROKEE ARCHER ee m Radio Equipment Optional Equipment cont Item Mark if Weight Arm In No Item Instl Pounds Aft Datum 178 Collins DCE 400 Distance Computing Equipment Cert Basis TSO C40a 2 1 58 9 179 Collins RCR 650 ADF Receiver and Antenna and IND 650 Indicator Cert Basis TSO C41c 6 6 104 8 180 Collins 650A ADF Receiver and antenna and IND 650A Indicator Basis TSO 41 m 7 3 100 3 181 Collins 350 Audio Marker Panel Cert Basis TSO C35d C50b 33 110 0 183 Collins TDR 950 Transponder Cert Basis TSO C74c 2 8 62 9 Weight includes antenna Weight includes antenna and cable ISSUED JUNE 18 1976 REPORT V REVISED MAY 23 1980 6 PIPER AIRCRAFT CORPORATION EIGHT AND BALA PA 28 181 CHEROKEE ARCHER nn m Radio Equipment Optional Equipment cont em Mark if Weight Arm In Moment 10 Instl Pounds Aft Dat
41. 4 4 Before ve e Sw E ea Oe are ere ens n pi 4 5 Mar IMP vere wheelie ented MM 4 5 Climb ionis Rr a feci 4 5 e esser T 4 5 Descent Normal sats 49 quaeret 4 5 Descent Power EUR 4 5 Approach And 4 6 Stopping Engine E aE EERS 4 6 Parking ite accents Re 4 6 4 7 Amplified Normal Procedures 4 7 4 9 Prefliehticheck sta e PANI slag ee 4 7 4 11 Before Starting 2 2 2 en ree a dr a aao RP ERR 4 8 ANS Starting Engine aussagen Kc Y ved xa qu EP RERO 4 9 4 Ra eA 4 11 4 Taxing cles de ate ee esa LIA ERA ae ERATES 4 11 449 Ground Check ds Sane Wanda tate Gee a ee OEE ener 4 11 ADL Before me bok oa iR RS RE EASIER 4 12 423 ae Led DT te CRI BOR P 4 12 4235 Climb 2 ns X Ud C Te s ae apr 4 13 427 Cruising occ cee cee e aues ae echas enr nnn n nnn 4 13 23 42080
42. 482 657 ISSUED JUNE 18 1976 PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER II SECTION AND BALANC Item No 113 115 117 119 12 123 k Instruments Optional Equipment Item Vacuum System Installation a With Airborne Model 211 Pump b With Edo Aire Model 1U128A Pump Cert Basis TC 2A13 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 Tru Speed Indicator Piper Spec 550049 30 Cert Basis TSO C2b Encoding Altimeter Piper PS50008 6 or 7 Cert Basis TSO C 0b C88 Altitude Digitizer Uniled Instrument P N 5125 P3 Cert Basis TSO C88 Vertical Speed Piper Dwg 99010 2 4 or 5 Cert Basis TSO C8b Alternate Static Source Cert Basis 2A13 Tum and Slip 1ndicator Piper 550030 2 or 3 Cert Basis TSO C3b Weight and moment difference between standard and optional equipment ISSUED JUNE 18 1976 REVISED MAY 23 1980 Mark if Weight Arm 1 Momei Instl Pounds Aft Datum Lb 1n lt 4 5 39 176 4 9 39 1 192 2 2 59 4 131 2 6 59 7 155 gt same as standard equiprnent 49 60 3 54 1 0 5125 52 1 0 65 9 6t x 4 61 0 2 x 2 6 59 7 15 REPORT 79 6 3 6 PIPER AIRCRAFT CORPORATION IGHT AND BALAN 28 181 CHEROKEE ARCHER Instruments Optional Equ
43. 7 23 Removed ELT information from 7 37 Added 8 29 Cold Weather Operation to table of contents Added 8 29 Cold Weather Operation Rev 5 761 624 PR780703 Ward Evans July 3 1978 REPORT VB 790 iv b PILOTS OPERATING HANDBOOK LOG OF REVISIONS cont Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev 6 761 624 1 6 Revised para 1 19 790228 1 12 1 13 Revised para 1 21 6 1 Revised para 6 1 6 33 Renumbered existing items 75 76 77 to 74 75 76 added new items 77 and 78 6 37 Revised item 113 6 41 Added item 178 7 10 Revised para 7 15 Warel Senn 7 11 Revised para 7 15 Ward 7 24 Revised para 7 37 Feb 28 1979 Rev 7 761 624 6 48 Revised item 279 Lad Gane PR790413 6 48a Added 280 Ward Evans 7 24 7 25 Revised para 7 37 April 13 1979 Rev 8 761 624 iti Revised applicability PR800523 Revised para 1 3 Revised para 1 1 Revised para 2 7 Revised para 2 11 Revised para 2 13 Added para 3 28 Added Carburetor icing Added para 3 28 Renumbered para added para 4 28 Added descent info moved info to pg 4 6 Relocated info from pg 4 5 Added para 4 28 Conti para 4 28 Added warning Revised para 5 5 Revised fig 5 15 Revised fig 5 23 Revised fig 5 24 Revised fig 5 25 Revised fig 5 26 Revised fig 5 27 Revised fig 5 29 Revised fig 5 31 Revised para 6 1 Added c
44. NOTE The remainder of the performance charts used in this flight plan example assume a no wind condition The effect of winds aloft must be considered by the pilot when computing climb cruise and descent performance c Climb The next step in our flight plan is to determine the necessary climb segment components The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the Time Distance and Fuel to Climb graph Figure 5 15 After the time distance and fuel for the cruise pressure altitude and outside air temperature values have been established apply the existing conditions at the departure field to the graph Figure 5 15 Now subtract the values obtained from the graph for the field of departure conditions from those for the cruise pressure altitude The remaining values are the true fuel distance and time components for the climb segment of the flight plan corrected for field pressure altitude and temperature The following values were determined from the above instructions in our flight planning example 1 Cruise Pressure Altitude 6000 ft 2 Cruise OAT 55 F 3 Time to Climb 11 5 min minus 3 min 8 5 min 4 Distance to Climb 16 minus 4 5 nautical miles 11 5 nautical miles 5 Fuelto Climb 2 gal minus gal reference Figure 5 11 reference Figure 5 35 reference Figure 5 15
45. ON py un ne du check RICH Carburetor heat s ea ON Primer zx onus locked If power is not regained proceed with power off landing ENGINE POWER LOSS IN FLIGHT switch to tank containing fuel Fuel selector Electre fuel pump us weed ar EE ON ter tori RICH POOR heat S des Sud ON Buse gauges es check for indication of cause of power loss Primer Dres eae check locked If no fuel pressure is indicated check tank selector position to be sure it is on a tank containing fuel When power is restored Carburetor heat soc eer Rs OFF Electric fuel pump ISSUED JUNE 18 1976 REVISED JULY 3 1978 power is not restored prepare for power off landing Trim for 76 KIAS POWER OFF LANDING Locate suitable field Establish spiral pattern 1000 ft above field at downwind position for normal landing approach When field can easily be reached slow to 66 KIAS for shortest landing Touchdowns should normally be made at lowest possible airspeed with full flaps When committed to landing Ignition Si Res tans iO TS Master switch OFF Fuelseleetor e ks OFF MIXTUNE aii nee ce ee idle cut off Seat beltandhames tight FIRE IN FLIGHT Source Of fire Electrical fire
46. Optional Equipment ame AEG OS 6 39 m Radio Equipment Optional Equipment 6 41 n Miscellaneous Optional Equipment 6 49 REPORT 790 64 PIPER AIRCRAFT CORPO SECTION 6 PA 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 61 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane it must be flown with the weight and center of gravity C G position within the approved operating range envelope Although the airplane offers flexibility of loading it cannot be flown with the maximum number of passengers full fuel tanks and maximum baggage With the flexibility comes responsibility the pilot m ensure that the airplane is loaded within the loading envelope before he makes takeoff Misloading carries consequences for any aircraft overloaded airplane will not take off climb or cruise as well as a properly loaded one The heavier the airplane is loaded the less climb performance it will have Center of gravity is a determining factor in flight characteristics 1f the C G is too far forward in any airplane it may be difficult to rotate for takeoff or landing If the is too far aft the airplane may rotate prematurely on takeoff or tend to pitch up during climb Longitudinal stability will be reduced This can lead to inadvertent stalls and e
47. PA 28 181 CHEROKEE ARCHER II PERFORMANCE 1331 W3IHUYB Ld 06 39NVISIQ 3440141 5 5 2 gt 1 1 N WIND KNOTS 5 a 5 us 3 3 Lu VT 12117 14114 De 2 u me o9 5 23 Nee B faeces e Ed 2053 OE 8 456548 c N E PRES I 548564 2812 8 lt 5 ok nw mo bad EB Sel lt 2 484 8 T 1 FLAPS UP TAKEOFF PERFORMANCE Figure 5 5 ISSUED JUNE 18 1976 REPORT VB 790 5 13 PIs 06L 8A LuOdiH 9L61 81 ANNE 030551 L S AAOTNVLSAVLI sc 28 181 35 PERFORMANCE H THROTTLE I TI OFF 59 FT h IN x 1 I T A au LZ 71 7 TL EYA 72278772104 irat LV LZ vA 1717
48. This User Manual supplies the information necessary for the efficient operation of the airplane when the ADF KR 87 is installed The information contained within this Supplement must be used in conjunction with the complete AFM This User Manual is a permanent part of this AFM and must remain in this AFM at all times when the ADF KR 87 is installed 2 LIMITATIONS No change 3 EMERGENCY PROCEDURES No change 4A NORMAL OPERATING PROCEDURES OPERATING PROCEDURES 4B ABNORMAL OPERATING PROCEDURES TO PROCEDURES No change 5 PERFORMANCE No change AFM M26 29 2005 4 Diamond MAINTENANCE AFM M26 KR87 6 MASS AND BALANCE Upon removal or installation of the ADF System KR 87 the change of empty mass and corresponding center of gravity of the airplane must be recorded according to Chapter 6 of the Airplane Flight Manual 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7 14 AVIONICS The Bendix King Digital ADF is a panel mounted digitally tuned automatic direction finder It is designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1799 kHz and eliminates the need for mechanical band switching The system is comprised of a receiver a built in electronics timer a bearing indicator and a KA 44B combined loop and sense antenna Operating controls and disp
49. Vent System Piper Dwg 76304 9 Cert Basis TC 2A13 6 4 159 6 1022 329 Overhead Vent System with Ground Ventilating Blower Piper Dwg 76304 10 Cert Basis TC 2A13 14 9 72 2 2566 331 Assist Step Piper Dwg 65384 Cert Basis TC 2413 S 1 8 156 0 281 333 Super Cabin Sound Proofing Piper Dwg 79601 3 Cert Basis TC 2A13 18 1 86 8 1571 335 Adjustable Front Seat Left Piper Dwg 79591 0 79591 2 Cert Basis TC 2A13 6 6 80 7 533 Adjustable Front Seat Right Piper Dwg 79591 1 79591 3 Cert Basis TC 2A13 6 8 80 0 544 Weight and moment difference between standard and optional equipment ISSUED JUNE 18 1976 REPORT E REVISED JULY 12 1977 ECTION 6 EIGHT AND n tem No 45 49 Weight and moment difference between standard and optional equipment Miscellaneous Optional Equipment cont Item Headrests 2 Front Piper Dwg 79337 18 Cert Basis TC 2A13 Headrests 2 Rear Piper Dwg 79337 18 Cert Basis TC 2A13 Inertia Safety Belts Rear 2 0 8 Ibs each Piper PS50039 4 14 Cert Basis TC 2A13 Assist Strap Piper Dwg 79455 Cert Basis TC 2A13 Deluxe Carpeting Cert Basis TC 2A13 Fire Extinguisher a Piper Dwg 76167 2 Scott 42211 00 b Piper Dwg 37872 2 Graviner 1014 01 Cert Basis TC 2A13 VB 790 50 Mark if Instl PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER
50. a case of malfunction ACTIVATE disconnect switch located above the ignition switch to OFF position b In case of malfunction overpower the electric trim at either control wheel Maximum altitude change with a 4 second delay recovery initiation is 800 feet and occurs in the descent configuration Maximum altitude change in the approach configuration with a 4 second recovery delay is 100 feet SECTION 4 NORMAL PROCEDURES The electric trim system may be turned ON or OFF by a switch located above the ignition switch The pitch trim may be changed when the electric trim system is turned on either by moving the manual pitch trim control wheel or by operating the trim control switch on the pilot s control yoke To prevent excessive speed increase in the event of an electric trim Tun away malfunction the system incorporates an automatic disconnect feature which renders the system inoperative above approximately 143 KIAS The disconnected ition does not affect the manual trim system SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED JUNE 18 1976 REPORT VB 790 REVISED MARCH 30 1984 9 13 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS 28 181 CHEROKEE ARCHER II THIS PAGEINTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 3 14 SECTION 10 SAFETY TIPS SECTION 10 SAFETY TIPS
51. and Code Rev 4 761 624 PR770712 cont Description of Revision Added relocated items renumbered items added new items revised item 277 relocated items added footnotes Added page added relocated items and new item Added page Renumbered items revised items 325 and 329 Renumbered items revised item 349 VE Added new propeller model to 7 5 Revised alternate static source description Ward Evans July 12 1977 in para 7 21 Revised note Revised propeller tolerance RPM Added additional Takeoff Check List Added Primer information to Engine Power Loss During Takeoff check list Added Primer information to Engine Power Loss During Takeoff Added Primer information to Before Takeoff check list Deleted pressing in of magneto switch as necessary Added Primer checked information to para graph Changed item 5 from Cruise Fuel to Cruise Fuel Consumption Added note to graph Added note to graph Added note to graph Added note to graph Changed paragraph Changed item 93 Added Collins VHF 250 to item 169 added Collins VIR 350 to item 171 Relocated item 187 189 and 191 added items to 189 and 191 Relocated item 187 189 and 191 added items 194 and 195 changed item 195 to 196 Relocated items 201 203 and 205 revised item 211 Added vendor information to iter 349 Added Caution to
52. and check Baggage close and secure for water sediment Fuel strainer na drain and proper fuel Primary flight controls proper operation Fuel vents dr a ets open Eabin door xcu roue xe Us close and secure Main gear 517005 2 proper Required papers on board inflation 4 50 in Seat belts and harness fastened adjust THES 2a SOR GER YE ERE PA RN check check inertia reel REPORT VB 790 ISSUED JUNE 18 1976 REVISED 30 1984 PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER SECTION 4 NORMAL PROCEDURE BEFORE STARTING ENGINE Braked eu mo 5 50 gt set Carburetor uu full COLD Fuel selector desired tank STARTING ENGINE WHEN COLD 2222 1 4 open Masterswitch ON Electric fuel pump ON MIXTE ns wenn E ROMS full RICH I 34 E Br DL LL engage ne ne adjust Oilipressure ae we ee check If engine does not start within 10 sec prime and repeat starting procedure STARTING ENGINE WHEN HOT Throttle x ost ee Aare 1 2 open Masterswiteli ex ON Electncifuelkpump ON Mixtures woes or E full RICH es voee vm pe vae RE engage THEO A Ew ev
53. anzubringen Kopie Normalverfahren Normal Procedures Start und Landung auf Tank rechts durchf hren wenn Autobenzin oder ein Gemisch aus Autobenzin und AVGAS 100 LL verwendet wird Tankwahlschaller Kraftstoff Planung Krafistoff Zusatz pumpen Funktionskontrolle der Pumpen vor dem Anlassen Die Tankwahlschaltung soll so gew hlt werden dass bei Verwendung von Auto Benzin und einer Aussentemperatur OAT von mehr als 30 C ein Kraftstoff Vorrat von mindestens des Beh ltervolumens f r den normalen Betrieb verbleibt Es sind 2 elektrisch betriebene Zusatzpumpen nr 1 und Nr 2 eingebaut die durch Schalter em Instrumenienbrett eingeschaltet werden Eine dieser Pumpen muss bei Rollen Start Steigflug oder Landung einge schaltet sein Schaller W hrend des Reisefluges ausreichender Kraftstoffdruck vorausgesetzt kann diese Pumpe ausgeschaltet werden Schalierstellung OFF Vgl auch Beschr nkungen Limitations im Originalhandbuch des Flugzeuges Zur gleichm ssigen Nutzung der Pumpen im Interesse der Betriebssicherheit wird die wechselweise Verwendung der Pumpen empfohlen einschalten und die Pumpen Nr 1 und Nr 2 nacheinander einschallen Jeweils Funktion durch H ren des Pumpenlaufger usches und des Kraftstofidruckes jeder Pumpe berpr fen Pumpe wieder ausschallen Notverfahren Emergency Procedures Vom Luftfahri Bundesamt g
54. baggage cargo and passengers Following this is the method for computing takeoff weight and C G ISSUED JUNE 18 1976 REPORT 790 REVISED MARCH 30 1984 6 1 SECTION 6 PIPER CORPORATION WEIGHT AND BALANCE 28 18 ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK EPORT VB 790 ISSUED JUNE 18 1976 2 PIPER RATION SECTION 6 28 181 CHEROKE RCHER II WEIGHT AND BALANCE 6 3 AIRPLANE WEIGHING PROCEDURE At the time of licensing Piper Aircraft Corporation provides each airplane with the basic empty weight and center of gravity location This data is supplied by Figure 6 5 The removal or addition of equipment or airplane modifications can affect the basic empty weight and center of gravity The following is a weighing procedure to determine this basic empty weight and center of gravity location Preparation 1 Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane 2 Remove excessive dirt grease moisture foreign items such as rags and tools from the airplane before weighing 3 Defuel airplane Then open all fuel drains until all remaining fuel is drained Operate engine on each tank until all undrainable fuel is used and engine stops Then add the unusable fuel 2 0 gallons total 1 0 gallons each wing CAUTION Whenever the fuel system is completely drained and fuel is re plenishe
55. be opened daily prior to first flight to check for water or sediment Each tank 125 an individual drain at the bottom inboard rear corner fuel strainer located on the lower left front of the fire wall has drain which is accessible from jutside the nose section The strainer should also be drained before the first flight of the day Refer to yaragraph 8 21 for the complete fuel draining procedure REPORT 790 ISSUED JUNE 18 1976 7 8 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 181 CHEROKEE ARCHER II DESCRIPTI N AND OPERATION B P ME ELECTRIC FUEL PUMP ENGINE FUEL PUMP CFG PRIMER FUEL STRAIMER LEFT MAIN FUEL TANK SELECTOR YALYE RIGHT MAIN TANK FUEL QUANTITY GAUGES FUEL SYSTEM SCHEMATIC Figure 7 9 ISSUED JUNE 18 1976 REPORT is SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND PA 28 181 CHEROKEE ARCHER e nn nn Fuel quantity and pressure are indicated on gauges located in a cluster on the left side of the instrument panel An engine priming system is provided to facilitate starting The primer pump is located to the immediate left of the throttle quadrant refer to Figure 7 5 7 15 ELECTRICAL SYSTEM The electrical system includes a 14 volt 60 amp alternator a 12 volt battery a voltage regulator an overvoltage relay and a master switch relay Figure 7 11 The battery is mounted in a thermoplastic box immediately aft
56. be restored by pressing the small clear plastic reset button located on the top of the front face of the ELT and then moving the switch to ARM 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 and ARMED The switch is normally in the ARMED position Moving the switch to ON will activate the transmitter Moving the switch back to the ARMED position will turn off the transmitter only if the impact switch has not been activated Optional equipment REPORT VB 790 ISSUED JUNE 18 1976 7 24 REVISED APRIL 13 1979 PIPER AIRCRAFT CORPORATION 7 28 181 ARCHER DESCRIPTION AND OPERATION The ELT should be checked to make certain the unit has not been activated during the ground check Check by selecting 121 50 MHz on an operating receiver If there is an oscillating chirping sound the ELT may have been activated and should be turned off immediately This requires removal of the access cover and moving the switch to OFF then press the reset button and return the switch to ARM Recheck with the receiver to ascertain the transmitter is silent CIR 11 2 OPERATION On the unit itself is a three position selector switch placarded OFF ARM and ON The ARM position is provided to set the unit to the automatic position so that it will transmit only after impact an
57. magneto switch clockwise When the engine fires release the magneto switch and move the throttle to the desired setting c Starting Engine When Flooded The throttle lever should be full OPEN the master switch and tum OFF the electric fuel pump Move the mixture control lever to idle cut off and engage the starter by TOfating the magneto switch clockwise When the engine fires release the magneto switch advance the mixture and retard the throttle d Starting Engine With External Power Source optional feature called the Piper External Power PEP allows the operator to use an external battery to crank the engine without having to gain access to the airplane s battery Turn the master switch OFF and tum all electrical equipment OFF Connect the RED lead of the PEP kit jumper cable to the POSITIVE terminal of an external 12 volt battery and the BLACK lead to the NEGATIVE terminal Insert the plug of the jum per cable into the socket located on the fuselage Note that when the plug is inserted the electrical System is ON Proceed with the normal starting technique After the engine has started reduce power to the lowest possible RPM to reduce sparking and disconnect the jumper cable from the aircraft Turn the master switch ON and check the alternator ammeter for an indication of output DO NOT ATTEMPT FLIGHT IF THERE 15 NO INDICATION OF ALTERNATOR OUTPUT NOTE For all normal operations usin
58. provided to replace the heat lost by vaporization Carburetor heat should be full on when carburetor ice is encountered Adjust mixture for maximum smoothness 3 29 ENGINE ROUGHNESS Engine roughness 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 power may not be possible therefore prompt action is required Turn carburetor heat on See Note RPM will decrease slightly and roughness will increase Wait for a decrease in engine roughness or an increase in RPM indicating ice removal If no change in approximately one minute return the carburetor heat to OFF If the engine is still rough adjust the mixture for maximum smoothness The engine will run rough if too rich or too lean The electric fuel pump should be switched to and the fuel selector switched to the other tank to see if fuel contamination is the problem Check the engine gauges for abnormal readings If any gauge readings are abnormal proceed accordingly Move the magneto switch to L then to the back to BOTH If operation is satisfactory on either magneto proceed on that magneto at reduced P with mixture full RICH to a landing at the first available airport If roughness persists prepare for a precautionary landing at pilot s discretion NOTE Partial carburetor heat may be worse than no heat
59. slip knots NOTE Additional preparations for high winds include using tie down ropes from the landing gear forks and securing the rudder 6 Install a pitot head cover if available Be sure to the pitot head cover before flight 7 Cabin and baggage doors should be locked when the airplane is unattended ISSUED JUNE 18 1976 REPORT SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICINu AND MAINTENANCE 28 181 CHEROKEE ARCHER II i nn 8 11 ENGINE AIR FILTER a Removing Engine Air Filter 1 Remove the lower cowl 2 Remove the wing nuts securing the filter Remove the filter b Cleaning Engine Air Filter The induction air filter must be cleaned at least once every 50 hours and more often even daily when operating in dusty conditions Extra filters are inexpensive and a spare should be kept on hand for use as a rapid replacement To clean the filter 1 Tap the filter gently to remove dirt particles being careful not to damage the filter Di NOT wash the filter in any liquid DO NOT attempt to blow out dirt with compressed air 2 If the filter is excessively dirty or shows any damage replace it immediately 3 Wipe the filter housing with a clean cloth and install the filter The usable life of the filter should be restricted to one year or 500 hours whichever comes first c Installation Of Engine Air Filter After cleaning or when replacing the filter install the filter in th
60. smoke in cabin Master switch E TIO OFF sao bue IM e open Cabin Heat u aa eaten Land as soon as practicable Engine fire Euelsel ctot un a CLOSED Mixtures unse as idle cut off Electric fuel pump check OFF Heater and defroster OFF Proceed with power off landing procedure LOSS OF OIL PRESSURE Land as soon as possible and investigate cause Prepare for power off landing REPORT VB 790 3 3 SECTION 3 EMERGENCY PROCEDURES TRAFT CORPORATION HEROKEE ARCHER II PIPER 28 1 LOSS OF FUEL PRESSURE Electric fuel pump Fuel selector HIGH OIL TEMPERATURE Land at nearest airport and investigate the problem Prepare for power off landing ALTERNATOR FAILURE Verify failure Reduce electrical load as much as possible Alternator circuit breakers rne check Alt switch OFF for 1 second then on If no output Altswitch ese sre sse si ne ren hmt t Reduce electrical load and land as soon as practical SPIN RECOVERY Throttle eer m m ntn idle Ailerons neutral ea anne full opposite to direction of rotation Control full forward neutral when rotation stops Control wheel as required to smoothly regain leve
61. switched to the position 4 28 DESCENT NORMAL To achieve the performance on Figure 5 29 the power on descent must be used The throttle should be set for 2500 RPM mixture full rich and maintain an airspeed of 122 KIAS In case carburetor ice is encountered apply full carburetor heat REPORT VB 790 ISSUED JUNE 18 1976 13 REVISED MAY 23 1980 PIPER CORPORATION SECTION 4 NORMAL PROCEDURES 28 181 HEROKEE ARCHER II POWER OFF If a prolonged power off descent is to be made apply full carburetor heat prior to power reduction if icing onditions are suspected Throttle should be retarded and mixture control leaned as required Power response hould be verified approximately every 30 seconds by partially opening and then closing the throttle clearing engine When leveling off enrichen mixture set power as required and select carburetor heat off unless carburetor icing conditions are suspected 4 29 APPROACH AND LANDING Check to insure the fuel selector is on the proper fullest tank and that the seat backs are erect The seat belts and shoulder harness should be fastened and adjusted and the inertia reel checked NOTE If the fixed shoulder harness non inertia reel type is installed it must be connected to the seat belt and adjusted to allow proper accessibility to all controls including fuel selector flaps trim etc while maintaining adequate restraint for the occupant
62. 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 supplies an action sequence for normal operations with little emphasis on the operation of the systems The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them This portion of the section is not intended for use as an in flight reference due to the lengthly explanations The short form check list should be used for this purpose 4 3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the safe operation of the airplane These figures are for standard airplanes flown at gross weight under standard conditions at sea level Performance for a specific airplane may vary from published figures depending upon the equipment installed the condition of the engine airplane and equipment atmospheric conditions and piloting technique Best Rate of Climb Speed 76 KIAS Best Angle of Climb Speed 64 KIAS Turbulent Air Operating Speed See Subsection 2 3 113 KIAS Maximum Flap Speed 102 KIAS e Landing Final Approach Speed Flaps 40 66 KIAS f Maximum Demonstrated Crosswind Velocity 17 KTS ISSUED JUNE 18 1976 REPORT 790 4 1 PIPER RAFT CORPORATION SECTION 4 NORMAL PROCEDURES PA 28 18 _ HEROKEE ARCHER
63. 110 Cert Basis E286 17 Alternator 60 Amp Chrysler 3656624 b Chrysler 4111810 ISSUED JUNE 18 1976 REVISED 23 1980 Mark if Instl X Weight Pounds 281 0 285 0 3 3 2 8 12 4 13 5 SECTION WEIGHT AND BALANCE Arm In Moment Datum Lb In 20 9 5873 20 9 5957 35 5 117 35 5 99 14 0 174 14 0 189 REPORT VB 790 6 19 PIPER AIRCRAFT CORPORATION ECTION 6 EIGHT AND PA 28 181 CHEROKEE ARCHER THIS INTENTIONALLY LEFT BLANK VB 790 ISSUED JUNE 18 1976 20 PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER II SECTION 6 WEIGHT AND BALANCE 5 en c Landing Gear and Brakes Item No 27 29 ISSUED JUNE 18 1976 Mark if Weight Arm In Item Instl Pounds Aft Datum Two Main Wheel Assemblies Piper Dwg 63370 0 amp 1 a Cleveland Aircraft Products Wheel Assembly No 40 86 Brake Assembly No 30 55 Cert Basis TSO C26a Two Main 4 Ply Rating Tires 6 00 6 with Regular Tubes Cert Basis TSO C62 One Nose Wheel Cleveland Aircraft Products Wheel Assembly No 40 76B Less Brake Drum Cert Basis TSO C26a 4 3 31 0 McCauley Industrial Corp Wheel Assy No D 30625 Cert Basis TSO C26b 5 5 31 0 One Nose Wheel 4 Ply Rating Tire 6 00 6 wi
64. 13 2 millibars Altitude measured from standard sea level pressure 29 92 in Hg by a pressure or barometric altimeter It is the indicated pressure altitude corrected for position and instrument error In this handbook altimeter instrument errors are assumed to be zero Actual atmospheric pressure at field elevation The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds ISSUED JUNE 18 1976 REVISED MARCH 30 1984 PIPER AIRCRAFT CORP PA 28 181 CHEROKEE HER SECTION 1 GENERAL c Power Terminology Takeoff Power Maximum Continuous Power Maximum Climb Power Maximum Cruise Power d Engine Instruments EGT Gauge Maximum power permissible for takeoff Maximum power permissible continuously during flight Maximum power permissible during climb Maximum power permissible during cruise Exhaust Gas Temperature Gauge e Airplane Performance and Flight Planning Terminology Climb Gradient Demonstrated Crosswind Velocity Accelerate Stop Distance Route Segment ISSUED JUNE 18 1976 REVISED MARCH 30 1984 The demonstrated ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during tak
65. 14 255 125 Audio Selector Panel Cert Basis TC 2A13 2 2 55 0 121 257 Narco CP 135 Audio Selector Panel Cert Basis TSO C50b 2 2 55 0 121 259 Narco CP 135M Audio Selector Panel Cert Basis TSO C50b C35d TEE 327 114 3 423 1 Narco DME 190 Cert Basis TC 2A13 Te SD 60 9 359 263 Narco DME 190 TSO Cert Basis TSO SD 60 9 359 265 Narco DME 195 Receiver and Indicator 132 154 5 2039 Cert Basis TSO Weight includes marker antenna and cable Weight includes antenna and cable REPORT VB 790 ISSUED JUNE 18 1976 6 47 REVISED JULY 12 1977 SCTION 6 EIGHT AND BALANCE P M 67 69 71 73 77 m Radio Equipment Optional Equipment cont Item Narco ADF 140 a Single b Dual Cert Basis TSO 41 Narco ADF 141 a Single b Dual Basis TSO 41 Narco AT50A Transponder Cert Basis TSO C74b a Narco AR 500 Altitude Encoder Cert Basis TSO C88 Narco AT150 Transponder Cert Basis TSO C74c a Narco AR 500 Altitude Encoder Cert Basis TSO C88 Antenna and Cable a Nav Receiving b 1 VHF Comm 2 VHF Comm d Glide Slope Single e Glide Slope Dual f Single ADF Sense Cert Basis TC 2A13 Anti Static Antenna and Cable 1 VHF Comm b 2 VHF Comm Single ADF Sense Cert Basis TC 2A13 Emergency Locat
66. 3 Example de 2300 ft Airport pressure altitu Gross weight 2264 Temperature 70 F Wind 5 knots headwind Landing distance 1290 ft ISSUED JULY 12 1977 REPORT VB 790 5 32 OL 01493 PIPER AIRCRAFT TION SECTION 5 PA 28 181 CHEROKEE AKcHER H PERFORMANCE 13 ONNOY9 em gt 1508 1400 1300 1200 1100 1000 00 0 TATA TTA ATA AHA ANA N WIN 8 3 8 Se 5 09 25 DIC 2 wu 5 2 2 58 5525 I 27828 5 00 2555111 5558 IT 11 se gauge 28283 ccs SESSE sraa eo 58855 BED BEP 5 LEW FELETI ES CONSE lt lt o o a a bez gt ys tes 51 s 1 Di LANDING GROUND ROLL Figure 5 35 SUED JULY 12 1977 REPORT VB 790 5 33 5 PIPER tAFT CORPORATION 28 181 ARCHER __ _ THIS INTENTIONALLY LEFT BLANK EPORT VB 790 ISSUED JULY 12 1977 34 SECT
67. 430 s GPS receiver is not authorized Use of the GNS 430 VOR ILS receiver to fly approaches not spproved for GPS require VOR ILS navigation data be present on the external indicator When an alternate airport is required by the applicable operating rules it must be served by approach based on other than GPS or Loran C navigation the aircraft must have the operational equipment capable of using that navigation aid and the required navigation aid must be operational VNAV information may be utilized for advisory information only Use of VNAY information for Instrument Approach Procedures does not guarantee step down fix altitude protection or arrival at approach minimums in normal position to land PIPER 2 190 00140 03 Rev C FAA APPROVED Page 6 of 10 DATE 11 21 02 5 GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER If not previously defined the following default settings must be made in the SETUP 1 menu of tho GNS 430 prior to operation refer to Pilot s Guide for procedure if necessary dis sels navigation units to nautical miles and knots b sets altitude units to feet and feet per minute map datum WGS 84 sets map datum to WGS 84 see note below d posn
68. 700 RPM 2700 RPM 75 to 245 F 245 60 PSI to 90 PSI 25 PSI to 60 PSI 25 PSI 90 PSI 5 PSI to 8 PSI 5 PSI 8 PSI NORMAL UTILITY 2550 LBS 2130 LBS 200 LBS 0 LBS weight as limited REPORT VB 790 2 3 SECTION 2 LIMITATIONS PIPERA RAFT CORPORATION 28 18 HEROKEE ARCHER ___ 2 13 CENTER OF GRAVITY LIMITS a Normal Category Weight Forward Limit Pounds Inches of Datum 2550 88 6 2050 and less 82 0 b Utility Category Weight Forward Limit Pounds Inches Aft of Datum 2050 and less 82 0 2130 83 0 NOTES Straight line variation between points given Rearward Limit Inches Aft of Datum 93 0 3 93 0 Rearward Limit Inches Aft of Datum 93 0 93 0 The datum used is 78 4 inches ahead of the wing leading edge at the inboard intersection of the straight and tapered section It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded See Section 6 Weight and Balance for proper loading instructions 2 15 MANEUVER LIMITS Normal Category acrobatic maneuvers including spins prohibited b Utility Category Approved maneuvers for bank angles exceeding 60 Steep Turns Lazy Eights Chandelles 247 FLIGHT LOAD FACTORS a Positive Load Factor Maximum b Negative Load Factor Maximum REPORT VB 790 24 Entry Speed 113 KIAS 113 KIAS 113 KIAS NORMAL UTILITY 3 8G 4 4 No inve
69. A 28 181 CHEROKEE ARCHER 73 75 76 77 78 Landirig Gear and Brakes Optional Equipment Item Nose Wheel Fairing Piper Dwg 65348 2 Cert Basis TC 2A13 Main Wheel Fairings Piper Dwg 65237 Cert Basis TC 2A13 Nose Wheel Fairing Piper Dwg 37896 3 Cert Basis TC 2A13 Main Wheel Fairings Piper Dwg 37885 2 3 Cert Basis TC 2A13 Nose Wheel Fairing Piper Dwg 37896 3 Cert Basis TC 2A13 Main Wheel Fairings Piper Dwg 79893 2 3 Cert Basis TC 2A13 ISSUED JUNE 18 1976 REVISED FEBRUARY 28 1979 Mark if Instl Weight Pounds 3 6 7 6 10 3 20 6 3 8 17 0 SECTION 6 WEIGHT AND BALANCE Ae A Arm In Moment Aft Datum 36 3 131 113 6 863 36 3 374 113 6 2340 36 3 138 113 6 1931 790 6 33 PIPER AIRCRAFT CORPORATION CTION 6 EIGHT AND BALAN PA 28 181 CHEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK EPORT 790 ISSUED JUNE 18 1976 34 PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER II OT Item No 79 81 83 85 87 89 91 93 95 97 99 Weight and moment difference between standard and optional equipment 0 Electrical Equipment Optional Equipment Item Instrument Panel Lights Cert Basis TC 2A13 Instrument Light Grimes 15 0083 7 Cert Basis TC 2A13 Cabin Light Cert Basis
70. AE Grades 1 All Temperatures 15W 50 or 20W 50 2 Above 80 F 60 60 3 Above 60 F 50 400 50 4 30 F to 90 F 40 40 5 O F to 70 F 30 30 40 or 20W 40 6 O Fto90 F 20W 50 20W 50 or 15W 50 7 Below 10 F 20 30 or 20W 30 When operating temperatures overlap indicated ranges use the lighter grade oil 1 11 MAXIMUM WEIGHTS NORMAL UTILITY a Maximum Takeoff Weight 065 2550 2130 Maximum Landing Weight 155 2550 2130 c Maximum Weights in Baggage Compartment 200 0 1 13 STANDARD AIRPLANE WEIGHTS a Standard Empty Weight 105 Weight of a standard airplane including unusable fuel full operating fluids and full 1416 b Maximum Useful Load lbs The difference between the Maximum Weight and the Standard Empty Weight 1134 1 15 BAGGAGE SPACE a Compartment Volume cubic feet 24 b Entry Width inches 22 c Entry Height inches 20 1 17 SPECIFIC LOADINGS a Wing Loading lbs per sq ft 15 0 Power Loading 165 per hp 14 2 These values are approximate and may vary from one aircraft to another Refer to Figure 6 5 for the Standard Empty Weight value and Useful Load value to be used for calculation for the aircraft specified REPORT 790 ISSUED JUNE 18 1976 1 4 REVISED JUNE 8 1990 PIPER AIRCRAFT CORP ATION SECTION 1 28 181 CHEROKEE GENERAL 1 19 SYMBOLS ABBREVIATIONS AND TERMINOLOGY The following defini
71. B 790 5 15 SECTION 5 PIPER CORPORATION PERFORMANCE 28 18 CHEROKEE ARCHER II 1333 1109 080099 130391 2 LIZLLIZI 4 d E e 5 gt 5 09 2 E S se 4 LZ T4 d 8 o 8 Ban S sus BRAGS 1 25300 amp 2585 5 BRE CES us Ies NN KIN SENN TTT gu cs Bs aab 0 E T 52 El gt e 3 25 FLAPS TAKEOFF GROUND ROLL Figure 5 11 REPORT VB 790 ISSUED JUNE 18 1976 5 16 PIPER AIRCRAFT TION SECTION 5 PA 28 181 CHEROKEE PERFORMANCE PA 28 181 72 A LIA VLVLVLELVILLLLLL 222 eee HH AlAs SZ Zl AI AUS ESSENER LAZ NA ZY 12414 17 20 0 20 40 60 80 100 200 400 600 800 1000 OUTSIDE AIR TEMP F RATE OF CLIMB F P M 20 0 0 10 30 OUTSIDE AIR TEMP 9 Example Climb pressure altitude 3600 ft OAT 30 F Rate of climb 620 F P M CLIMB PERFORMANCE Figure 5 13 ISSUED JUNE 18 1976 REPORT ns 5 SECTION 5 PIPER CORPORATION PERFORMANCE PA 28 181 CHEROKEE ARCHER II
72. CLUDES CLIMB TAT 55 Power 755 CIVI T 21112 AND DESCENT DISTANCE A LALUVLLLYTLLI HH a AL IAN VU IA LT LI ILLI rt HEN TULIT LT 11 7 18711 HAST VTT ATT TA NOTE ET LT YT TTA ARE EEEREN T ETES LT TT LIA 15 1 Zi SAH HH I RR FR A TA 1 1 A D A PL TVET TT an CT 0 50 80 100 F 400 500 00 500 500 700 0 20 pl gt 30 20 0 0 10 20 30 C OUTSIDE AIR TEMP Example pressure altitude 5500 ft se OAT 35 F Power setting 75 Range with reserve 480 nautical miles Range no reserve 535 nautical miles BEST POWER MIXTURE RANGE SERIAL NOS 28 7790001 THROUGH 7790607 Figure 5 23 ISSUED JUNE 18 1976 REPORT VB 790 REVISED MAY 23 1980 5 25 5 PIPER A CORPORATION ERFORMANCE PA 28 181 _HEROKEE ARCHER II m BEST POWER MIXTURE RANGE MIXTURE LEANED TO 1009 F RICH OF PEAK EGT 6 WHEEL FAIRINGS
73. E ms eee u II 1 1 D Miscellaneous Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In 65 Forward Seat Belts 2 Piper Spec 550039 4 2 Cert Basis TSO C22f 67 Rear Seat Belts 2 Piper Spec 550039 4 3 Cert Basis TSO C22f ISSUED JUNE 18 1976 REPORT VB 790 6 27 PIPER AIRCRAFT CORPORATION TION 6 GHT AND BALANC 28 181 CHEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK PORT VB 790 ISSUED JUNE 18 1976 8 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 181 CHEROKEE Wi4GHT AND BALANCE p Engine and Engine Accessories Optional Equipment Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED JUNE 18 1976 REPORT eri SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT ANDBAL PA 28 181 CHEROKEE ARCHER II THIS INTENTIONALLY LEFT BLANK EPORT VB 790 ISSUED JUNE 18 1976 30 PIPER AIRCRAFT CORPORATION SECTION 6 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE h Propeller and Propeller Accessories Optional Equipment Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In REPORT VB 79C ISSUED JUNE 18 1976 6 31 PIPER AIRCRAFT CORPORATION CTION 6 SIGHT AND BALAN PA 28 181 CHEROKEE ARCHER a THIS PAGE INTENTIONALLY LEFT BLANK PORT VB 790 ISSUED JUNE 18 1976 PIPER AIRCRAFT CORPORATION P
74. E 18 1976 REPORT VB 790 9 7 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS 28 181 CHEROKEE ARCHER d OMNI Tracker 1 Center Turn Command Knob and push IN to engage Tracker 2 Trim Knob push IN for high sensitivity 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 790 ISSUED JUNE 18 1976 9 8 PIPER AIRCRAFT CORPORATION SECTION PA 28 181 CHEROKEE ARCHER t SUPPLEMENT SUPPLEMENT 3 AUTOCONTROL AUTOPILOT INSTALLATION SECTION 1 GENERAL This supplement cupplies information necessary for the operation of the airplane when the optional Piper AutoControl IIIB Autopilot is installed The information contained within this supplement is to be used as described in conjunction with the complete handbook This supplement has been FAA Approved as a permanent part of this handbook and must remain in this handbook at all times with the optional Piper AutoControl IIIB Autopilot is installed SECTION 2 LIMITATIONS Autopilot use prohibited above 149 KIAS b Autopilot OFF during takeoff and landing SECTION 3 EMERGENCY OPERATION a an emergency the AutoControl can be disconnected by 1 Pushing the roll ON OFF Rocker Switch OFF 2 Pulling the Autopilot Circuit Breaker aircraft serial nos 28 7790001 through 28 7890475 only b The autopilot can be overpower
75. EPORT VB 790 ISSUED JUNE 18 1976 REVISED MARCH 20 1984 10 1 ECTION 10 PIPER AIRCRAFT CORPORATION PERATING TIPS PA 28 181 CHEROKEE ARCHER II o Extreme running turning takeoffs should be avoided as fuel flow interruption may occur Prolonged slips or skids which result in excess of 2000 ft of altitude 105 or other radical or extreme maneuvers which could cause uncovering of the fuel outlet must be avoided as fuel flow interruption may occur when tank being used is not full G Hand starting of the engine is not recommended however should hand starting of the engine be required only experienced personnel should attempt this procedure The magneto selector should be placed to LEFT during the starting procedure to reduce the probability of Kick Back Place the ignition switch to BOTH position after the engine has started EPORT VB 790 ISSUED JUNE 18 1976 2 REVISED MARCH 30 1984 n NT 38108 Braunschweig Anhang zum Flughandbuch f r PA 28 160 W Nr 28 671 bis 28 1760 28 1761 bis 28 4377 K 28 161 W Nr 28 7716001 bis 28 8116001 und h her 28 180 W Nr 28 671 bis 28 1760 28 1761 bis 28 5859 28 7105001 bis287505261 PA 28 181 W Nr 28 7690001 bis 28 7990626 28 8090001 bis 28 8590004 u h her Kennzeichen D Werk Nr ser Anhang muss dem offiziell genehmigten Flughandbuch des oben eingetragene
76. Figure 8 3 d Draining Fuel Strainer Sumps and Lines The fuel system sumps and strainer should be drained daily prior to the first flight and after refueling to avoid the accumulation of contaminants such as water or sediment Each fuel tank is equipped with an individual quick drain located at the lower inboard rear corner of the tank The fuel strainer is equipped with a quick drain located on the front lower comer of the firewall Each of the fuel tank sumps should be drained first Then the fuel strainer should be drained twice once with the fuel selector valve on each tank Each time fuel is drained sufficient fuel should be allowed to flow to ensure removal of contaminants This fuel should be collected in a suitable container examined for contaminants and then discarded CAUTION When draining any amount of fuel care should be taken to ensure that no fire hazard exists before starting the engine Each quick drain should be checked after closing it to make sure it has closed completely and is not leaking REPORT 790 ISSUED JUNE 18 1976 8 12 PIPER AIRCRAFT CORPORATION SECTION 8 PA 28 181 CHEROKEE ARCHER II HANDLING SERVICING AND MAINTENANCE e Draining Fuel System The bulk of the fuel may be drained from the system by opening the valve at the inboard end of each fuel tank Push up on the arms of the drain valve and turn counterclock wise to hold the drain open The remaining
77. ION 3 EMERGENCY PROCEDURES PA 28 1 81 HEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 3 6 PIPER AIRCRAFT CORP SECTION 3 PA 28 181 CHEROKEE Ax cHER EMERGENCY PROCEDURES 3 5 AMPLIFIED EMERGENCY PROCEDURES GENERAL The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of emergency situation 3 7 ENGINE FIRE DURING START Engine fires during start are usually the result of overpriming The first attempt to extinguish the fire is to try to start the engine and draw the excess fuel back into the induction system If a fire is present before the engine has started move the mixture control to idle cut off open the and crank the engine 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 seconds the fire should be extinguished by the best available external means The fuel selector valves should be OFF and the mixture at idle cut off if an external fire extinguishing methad is to be used 3 9 ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situa
78. ION 6 WEIGHT amp BALANCE SECTION 6 WEIGHT 4 BALANCE TABLE CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page No No 6 1 General cabe ws qe s qur eds ien es Ago cte suu rg ge oe had 6 1 C Airplane Weishing Procedure syr tiee ape De 6 3 Weigliteand Balance Data and Record Er a aah E Weg 6 6 6 7 Weight and Balance Determination for Flight 6 11 6 9 Equipment Bist we aan eke ae ce rn 6 17 Propeller and Propeller 5 5 6 17 b Engine and Engne ACcessones va owaniu e ay d due uoa AES 6 19 c Wanding G ar and Brakes iue c AREA xq eis 6 21 d Electrical Eg ipmett prt ur SOS ne soe ia d 6 23 e Iistr ments 3 xu Un y docte ud RN A 6 25 f Miscellaneous 2 0 5 mu ex B ee eS RAUS amr E OE 6 27 2 Engine and Engine Accessories Optional Equipment 6 29 1 Propeller and Propeller Accessories Optional Equipment 6 31 1 Landing Gear and Brakes Optional 6 33 0 Electrical Equipment Optional Equipment 6 35 Instruments Optional Equipment 6 37 1 Autopilots
79. ION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS 7 1 THE AIRPLANE The PA 28 181 Cherokee is a single engine low wing monoplane of all metal construction It has sur place seating two hundred pound baggage capacity and a 180 horsepower engine 7 3 AIRFRAME The basic airframe except for a tubular steel engine mount steel landing gear struts and other miscellaneous steel parts is of aluminum alloy construction The extremities the wing tips the cowling the tail surfaces are of fiberglass or ABS thermoplastic Aerobatics are prohibited in this airplane since the structure is not designed for aerobatic loads The semi tapered wings have a laminar flow type NACA 65 415 airfoil 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 providing in effect a continuous main spar with splices at each side of the fuselage There are also fore and aft attachments at the rear spar and at an auxiliary front spar 7 5 ENGINE AND PROPELLER The Cherokee 181 is powered by a four cylinder direct drive horizontally opposed engine rated at 180 horsepower at 2700 rpm It is furnished with a starter at 60 ampere 14 volt alternator a shielded ignition vacuum pump drive a fuel pump and a dry automotive type carburetor air filter The exhaust system is made entirely from stainless steel and is equipped w
80. NGE NAUTICAL MILES 500 500 30 20 10 0 10 20 30 C OUTSIDE AIR TEMP E ple Cruise pressure altitude 3000 ft Cruise OAT 35 F Power setting 65 Range with reserve 570 nautical miles Range no reserve 650 nautical miles BEST ECONOMY MIXTURE RANGE SERIAL NOS 28 7790001 THROUGH 7790607 Figure 5 25 LT 8 Se T 45 MIN RESERVE HEE EE EEE IT AT 55 POWER TT H H ILI T4 HHHH AT IAT TTT Le TATA um LII H 800 RANGE MAY REDUCED BY UP TO 4 WHEEL FAIRINGS ARE INSTALLED ISSUED JUNE 18 1976 REPORT VB 790 REVISED MAY 23 1980 5 27 PIPER RAFT CORPORATION ECTION 5 ERFORMANCE PA 28 181 HEROKEE ARCHER NENNEN Ea Po ilii PA 28 181 EST ECONOMY MIXTURE RANGE MIXTURE LEANED TO PEAK EGT WHEEL FAIRINGS INSTALLED 48 GAL USABLE FUEL 2550 POUNDS ZERO WIND RANGE INCLUDES CLIMB AND HH DESCENT DISTANCE MORE HEE EE EEE im RANGE WITH 45 MIN RESERVE f RANGE WITH 559 AT 55 POWER m
81. OC GS Indicator Cert Basis TSO C34c C36c C40a 1 2 59 9 72 196 King KI 213 VOR LOC GS Indicator Cert Basis TC 2A13 23 60 4 151 197 King KI 214 VOR LOC GS Ind Cert Basis TC 2A13 T 3 3 59 9 198 199 King 74 Cert Basis TC 2A13 nn 4 7 56 6 266 1 King 61 DME Cert Basis TC 2A13 12 5 179 0 2237 203 King KN 65 DME Cert Basis TSO 13 0 174 9 2274 205 King KR 85 Digital ADF UU NE 8 6 85 2 733 0 8 51 0 41 Audio Amplifier Cert Basis TSO C41b ISSUED JUNE 18 1976 REVISED JULY 3 1978 REPORT VB 79C 6 43 CTION 6 PIPER AIRCRAFT CORPORATION IGHT AND BALAN PA 28 181 CHEROKEE ARCHER II ____ m Radio Equipment Optional Equipment cont m Mark if Weight Arm In Moment Instl Pounds Aft Datum Lb In 07 King 86 ADF First 6 7 91 6 614 b Second 9 7 107 0 1038 c Audio Amplifier 0 8 51 0 41 Cert Basis TC 2A13 29 King 20 Audio Panel Cert Basis TSO C35c C50b m 3 7 70 8 262 11 King KT 76 78 Transponder Cert Basis TSO C74b ERES 3 1 58 1 180 eight includes antenna and cable PORT VB 790 ISSUED JUNE 18 1976 REVISED JULY 3 1978 PIPER AIRCRAFT CORPORATION 28 1 81 CHEROKEE ARCHER II Item No 213 215 217 219 22 225 227 229 m Radio Equipment Optional Equipment cont
82. ODUCTION TO PERFORMANCE AND FLIGHT PLANNING The performance information presented in this section is based on measured Flight Test Data corrected to LC A O standard day conditions and analytically expanded for 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 the aircraft This performance however can be duplicated by following the stated procedures in a properly maintained airplane Effects of conditions not considered on the charts must be evaluated by the pilot such as the effect of soft or grass runway surface on takeoff and landing performance or the effect of winds aloft on cruise and range performance Endurance can be grossly affected by improper leaning procedures and inflight fuel flow and quantity checks are recommended REMEMBER To get chart performance follow the chart procedures The information provided by paragraph 5 5 Flight Planning Example outlines a detailed flight plan using the performance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes ISSUED JUNE 18 1976 REPORT REVISED MAY 23 1980 SECTION 5 PIPER CORPORATION PERFORMANCE 28 CHEROKEE ARCHER
83. Pilot ALL LED s Selected Radios Pilot Selected Radios Pilot OFF Copilot Copilot MONO STEREO HEADSETS If monaural headsets are plugged into stereo jacks that do not have a switch installed the unit will not be damaged One of the headset channel outputs will be shorted to ground under these conditions The person plugging in the mono headset will hear only one channel from the GMA 340 but in both ears However anyone else plugging in a stereo headset at different passenger position will have audio in one ear only unless his or her headset has a stereo mono switch Note that a stereo mono switch on the headset does not prevent the mono headset from shorting one of the channels to ground That headset only routes its tip audio to both ears MARKER RECEIVER The marker beacon is used as part of an ILS approach and in certain instances to identify an airway In addition to the normal marker beacon functions the GMA 340 provides an audio muting function The lamps illuminate and an associated keyed tone is heard when MKR audio is selected when the airplane passes over a 75 MHz marker beacon transmitter The lamp and audio keying for ILS approach operation are summarized below Audio Audio Keying Lamp Actuated Frequency 1300 Hz Amber Middle 3000 Hz White Airway lnner Rev 06 Feb 2006 4 Diamond MAINTENANCE Doc No AFM M10 GMA 340 The GMA 340 s marker beacon r
84. REVISED MARCH 30 1984 PIPER AIRCRAFT ON SECTION 6 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE MODEL 28 181 CHEROKEE ARCHER II Airplane Serial Number Registration Number Date AIRPLANE BASIC EMPTY WEIGHT Arm Weight Inches Aft Moment Item Lbs of Datum In Lbs Standard Empty Weight Compate Optional Equipment tup a Basic Empty Weight The standard empty weight includes full oil capacity and 2 0 gallons of unusable fuel AIRPLANE USEFUL LOAD Gross Weight Basic Empty Weight Useful Load Normal Category 2550 Ibs Ibs 155 Utility Category 2130 Ibs Ibs Ibs AIS BASIC EMPTY WEIGHT AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE WEIGHT AND BALANCE DATA FORM Figure 6 5 ISSUED JUNE 18 1976 REPORT VB 790 REVISED MARCH 30 1984 67 SECTION 6 PIPER RAFT CORPORATION WEIGHT AND BALANCE 28 18 ARCHER II ___ THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 5 8 SECTION 6 WEIGHT AND BALANCE welt 25 39 58 S d 5 3 22123 RE z z 8 Dad 5 5 23 TTT ELLTELLLLLELELLELEL
85. S a Number of Engines b Engine Manufacturer Engine Model umber d Rated Horsepower Rated Speed rpm Bore inches g Stroke inches h Displacement cubic inches 1 Compression Ratio Engine Type 15 PROPELLERS a Number of Propellers b Propeller Manufacturer c Model d Numberof Blades e Propeller Diameter inches 1 Maximum 2 Minimum f Propeller Type 17 FUEL AVGAS ONLY eed a Fuel Capacity 05 gal total b Usable Fuel Total c Fuel Grade Aviation 1 Minimum Octane 2 Specified Octane 3 Altemate Fuel 1 Oil Capacity U S Quarts b Oil Specification Serial nos 28 7790001 through 28 7790607 Serial nos 28 7890001 and up ISSUED JUNE 18 1976 REVISED JUNE 8 1990 SECTION GENERA Lycomin 0 360 4 or 360 4 18 270 512 4 37 361 0 8 5 1 Four Cylinder Direct Drive Horizontally Opposed Air Cooled 1 Sensenich 76 855 0 60 76 855 0 62 2 76 76 Fixed Pitch 250 48 100 130 100 130 Refer to latest issue of Lycoming Instruction No 1070 8 Refer to latest issue of Lycoming Instruction No 1014 790 1 3 SECTION 1 PIPERA RAFT CORPORATION GENERAL 28 18 ARCHER Oil Viscosity per Average Ambient Temp for Starting MIL L 6082B MIL L 22851 Mineral Ashless Dispersant SAE Grade S
86. S check Annunciator panel press to test Carburetor heats wo check Engine is warm for takeoff when throttle can be opened without engine faltering Electric fuel pump OFF Fuel pressure check Throttle ehe ae Tut retard ISSUED JUNE 18 1976 REVISED JULY 12 1977 PIPER AIRCRAFT CORPORATION SECTION 4 PA 28 181 CHEROKEE ARCHER NORMAL PROCEDURES BEFORE TAKEOFF SOFT FIELD Master switeh x22 en ON Sewn E 25 second notch Flight instruments check Accelerate to 41 to 49 KIAS depending on aircraft Fuelseleetor eam esed proper tank weight Electric fuel pump Control wheel back pressure to Engine gauges P check rotate to climb attitude Carburetorheat sa H FE After breaking ground accelerate to 45 to 54 KIAS Seat backs depending on aircraft weight Mixture ite set Accelerate to best flaps up rate of climb speed 76 3 Fm pP z locked KIAS Belts harness i neoe fastened adjusted Epsum Rated ar didus retract slowly Empty seats urs seat belts sn gly fastened Plaps 32 anat a eo n S bis set Trim uter set CLIMB Sw ee e aat free cU a NM latched Best rate flaps up 76 KIAS A rconditlonBr ne
87. SIDE AIR TEMP Example Cruise pressure altitude 5500 ft Cruise OAT 30 F Power setting 55 True airspeed 101 knots SPEED POWER PERFORMANCE CRUISE SERIAL NOS 28 7890001 AND UP Figure 5 20 REPORT 790 ISSUED JUNE 18 1976 5 22 REVISED JULY 12 1977 PIPER AIRCRAFT CORPO SECTION 5 PA 28 181 CHEROKEE ARUdER PERFORMANCE PA 28 181 SPEED POWER S HAH economy HH L BEST ECONOMY MIXTURE IN I EI 2550 LBS GR WT MIXTURE LEANED TO EGT UITI TT L WHEEL FAIRINGS INSTALLED 1 4 M RHR CH 20 0 20 40 60 80 100 90 100 110 120 130 OUTSIDE AIR TEMP TRUE AIRSPEED KNOTS 0 0 0 10 20 30 OUTSIDE AIR TEMP C Cruise pressure altitude 6000 ft Cruise OAT 55 F Power 65 True airspeed 110 knots SPEED POWER ECONOMY CRUISE SERIAL NOS 28 7790001 THROUGH 7790607 Figure 5 21 ISSUED JUNE 18 1976 REPORT VB 790 REVISED JULY 12 1977 5 23 PIPER 4 7RAFT CORPORATION 2814 CHEROKEE ARCHER PA 28 181 SPEED POWER ECONOMY CRUISE ECTION 5 ERFORMANCE VU ZZ ASA IZ 14 IAAT Vara PIA IM 1414 255018 MAX CROSS MIXIURE LEARED BAN WHEEL FAIRINGS INSTALLED HH 414
88. Seren DE FO ra QU 2 7 5 aus oir sex pM Xe i 7 6 715 PUEDEN eon eo en DAENNA IS Shei Wave Ra ore AE 7 8 215 BOCA SYS uus icm OS ER mmm on 7 10 297 cus di cxt emt une wa D 7 15 419 Initr mentP nel 4 5 5 gis cea eau ne 7 16 on npr UU ve m Eee 7 18 7 23 Heating and Ventilating 7 7 21 2 25 CABIN POADIA A F ENSE vues cce 7 21 VA XE R qu rm omm ya EH TO UNS ace 7 22 Va SB NADIE Qi au ep mj Os ebrei Oan DRITTE Dr DT HIS 7 22 9 na e voe es cues ales RE HE He A 7 22 299 cu su tia vu eor ee ws ratu s 7 23 7 39 Piper Extemal Power 3 acd DA DS D 7 24 237 Emergency Locator Transmitter PM QNI Ra 7 24 790 74 AIRCRAFT CORPORATION SECTION 7 28 181 CHEROKEE ARCHER IT AND OPERATION SECTION 7 DESCRIPT
89. T DS w e 455 SIS E m 25 E o 5 B Ey YY Regis Voy Cz Zn gt 4 gt s Description of Article or Modification Scrial Number PA 28 181 WEIGHT AND BALANCE RECORD Figure 6 7 ISSUED JUNE 18 1976 REPORT 790 REVISED MARCH 30 1984 59 SECTION 6 PIPER RAFT CORPORATION WEIGHT AND BALANCE 28 18 H t Empty Weight Running Basic Page Number Removed Weight Change Added lt gt re PLLC WEIGHT AND BALANCE RECORD cont Figure 6 7 cont Registration Number Description of Article or Modification Serial Number PA 28 181 Item No t Date REPORT VB 790 ISSUED JUNE 18 1976 6 10 REVISED MARCH 30 1984 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE 6 7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT Add the weight of all items to be loaded to the basic empty weight b Use the Loading Graph Figure 6 13 to determine the moment of all items to be carried in the airplane c Add the moment of all items to be loaded to the basic empty weight moment d Divide the total moment by the total weight to determine the location e By using the figures of item a and item d above lo
90. TION Revised page nos revised titles added pages added figures Added ser nos Relocated Fig 5 19 to page 5 21 added new chart Fig 5 18 Relocated Fig 5 21 to page 5 23 added re located Fig 5 19 added ser nos Relocated Fig 5 23 to page 5 25 added new chart Fig 5 20 Relocated Fig 5 25 to page 5 27 added re located Fig 5 21 added ser nos Relocated Fig 5 27 to page 5 29 added new chart Fig 5 22 Relocated Fig 5 29 to page 5 30 added re located Fig 5 23 added ser nos Relocated Fig 5 31 to page 5 31 added new chart Fig 5 24 Relocated Fig 5 33 to page 5 32 added re located Fig 5 25 added ser nos Relocated Fig 5 35 to page 5 33 added new chart Fig 5 26 Added page added relocated Fig 5 27 Added page added relocated Fig 5 29 Added page added relocated Fig 5 31 Added page added relocated Fig 5 33 Added page added relocated Fig 5 35 Added page int blank Added item 3 Added items 76 and 77 Added item 223 renumbered items re located item Added relocated items renumbered items added new items relocated items removed footnotes added footnote Added relocated items renumbered items added new items relocated items added footnote REPORT 790 iv a PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revised Pages Approval Signature and Date Revision Number
91. TRANSPONDER MARKER BEACON AUDIO SELECTOR PANEL TRANSCEIVERS ADF RECEIVER DME RECEIVER ENGINE HOUR METER SUCTION GAUGE HEAT amp DEFROST CONTROL CIGAR LIGHTER MIKE JACK PHONE JACK AUTOPILOT ENGINE INSTRUMENT CLUSTER OMNI COUPLER SWITCH MAGNETO 4 STARTER SWITCH PITCH CONTROL MANIFOLD PRESSURE GAUGE TACHOMETER FUEL GAUGES PRIMER MICROPHONE THROTTLE QUADRANT FRICTION LOCK CARBURETOR HEAT CONTROL EGT INDICATOR INSTRUMENT PANEL LIGHTS CIRCUIT BREAKER PANEL CLIMATE CONTROL L NOLLO3S PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION AND _ ATION PA 28 181 CHEROKEE ARCHER II 7 21 PITOT STATIC SYSTEM The system supplies both pitot and static pressure for the airspeed indicator altimeter and the optional vertical speed indicator Figure 7 17 Pitot and static pressure are picked up by a pitot head installed on the bottom of the left wing and carried through pitot and static lines within the wing and fuselage to the gauges on the instrument panel An alternate static source is available as optional equipment The control valve is located below the left side of the instrument panel When the valve is set in the altemate position the altimeter vertical speed indicator and airspeed indicator will be using cabin air for static pressure The storm window a
92. TRICAL STORMS In the vicinity of electrical storms an ADF Indicator pointer tends to swing from the station tuned toward the electrical discharges Location of the storm can be useful information but the erratic behavior of the pointer should be taken into account NIGHT EFFECT This is a disturbance particularly strong just after sunset and just after dawn An ADF indicator pointer may swing erratically at these times If possible tune to the most powerful station at the lowest frequency If this is not possible take the average of pointer oscillations to determine relative station bearing MOUNTAIN EFFECT Radio waves reflecting from the surface of mountains may cause the pointer to fluctuate or show an erroneous bearing This should be taken into account when taking bearings over mountainous terrain COASTAL REFRACTION Radio waves may be refracted when passing from land to sea or when moving parallel to the coastline This should be taken into account when operating near coastal areas 8 AIRPLANE HANDLING CARE AND MAINTENANCE No change AFM M26 Rev 29 Nov 2005 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR PIPER PA32 WITH GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER 24 Reg Et SN TS 346 This Supplement must be attached to the FAA Approved Airplane Flight Manual when the GARMIN GNS 430 VHF Communication Transceiver VOR ILS Receiver Global Positioni
93. When the timer reaches 00 it will start to count up as the display flashes for 15 seconds and an aural alarm is activated for about 1 second NOTE The standby frequency which is in memory while flight time or elapsed time modes are being displayed maybe called back by pressing the button then transferred to active use by pressing the FRQ button again While FLT or ET is displayed the in use frequency on the left side of the window may be changed by using the frequency select knobs without any effect on the stored standby frequency or the other modes This feature is especially useful when searching for stations with unknown frequencies ERRONEOUS ADF BEARINGS DUE TO RADIO FREQUENCY PHENOMENA STATION OVERLAP In the U S the FCC which assigns AM radio frequencies occasionally will assign the same frequency to more than one station in an area Certain conditions such as Night Effect may cause signals from such stations to overlap This should be taken into consideration when using AM broadcast stations for naviation Sunspots and atmospheric phenomena may occasionally distort reception so that signals from two stations on the same frequency will overlap For this reason it is always wise to make positive identification of the station being tuned by switching AFM M26 Rev 29 Nov 2005 4 Diamond MAINTENANCE Doc No AFM M26 KR87 the function selector to ANT and listening for station call letters ELEC
94. Y 5 NOISU3AIQ LY3H COH LNOO TOU LNOD 5 1374n0 15 1374n0 LSNVHXA 49N0 ATanassv 5 e m9 uio ISSUED JUNE 18 1976 Figure 7 19 REPORT VB 790 7 20 PIPER AIRCRAFT CORPORATION _ SECTION 7 28 181 CHEROKEE ARCHER DESCRIPTION AND OPERATION 7 23 HEATING AND VENTILATING SYSTEM Heat for the cabin interior and the defroster system is provided by heater muff attached to the exhaust system Figure 7 19 The amount of heat desired can be regulated with the controls located on the far right side of the instrument panel The air flow can be regulated between the front and rear seats by levers located on top of the heat ducts next to the console Fresh air inlets are located in the leading edge of the wing near the fuselage An adjustable outlet is located on the side of the cabin near the floor at each seat location overhead air outlets are offered as tional equipment Air is exhausted through an outlet under the rear seat cabin air blower ucorporated in the ventilating system is also available as optional equipment An optional overhead ventilating system with a cabin air blower is available on models without air conditioning This blower is operated by a
95. air is encountered or expected the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and 10 allow for inadvertent speed build ups which may occur as a result of the turbulence or of distractions caused by the conditions See Subsection 2 3 4 39 WEIGHT AND BALANCE It is the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs center of gravity envelope while in flight For weight and balance data refer to Section 6 Weight and Balance REPORT VB 790 ISSUED JUNE 18 1976 4 16 SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph No TA GORGES ans ogs BIS ETT Introduction to Performance and Flight Planning 5 5 Flight Planning Example i i co 54 cs te ae 57 Performance Graphs s se oii id s or o s rs 5 6 0 REPORT VB 790 54 PIPER AIRCRAFT SECTION 5 28 181 SECTION 5 PERFORMANCE 5 1 GENERAL All of the required FAA regulations and complementary performance information applicable to the Cherokee Archer is provided by this section erformance information associated with those optional systems and equipment which require he vok supplements is provided by Section 9 Supplements 5 3 INTR
96. ana En ZL LZ ILELLELILLLECLCULL HHHH SE HA HERE Hrn HH MEAN HE III HA AEE HHH ALIA LL y a VEIT 2 20 20 40 60 100 F 500 500 700 600 700 800 RANGE NAUTICAL MILES RAMGE BE REDUCED UP TO 8 IF WHEEL FAIRNGS ARE NOT INSTALLED 4 30 20 10 0 10 20 30 40 C OUTSIDE AIR TEMP xam ple Cruise pressure altitude 3000 ft Cruise OAT 35 F Power setting 65 Range with reserve 600 nautical miles Range no reserve 670 nautica miles BEST ECONOMY MIXTURE RANGE SERIAL NOS 28 7890001 AND UP Figure 5 26 EPORT VB 790 ISSUED JUNE 18 1976 28 REVISED MAY 23 1980 PIPER AIRCRAFT CORPO TION SECTION 5 PA 28 181 CHEROKEE II PERFORMANCE 28 181 ENDURANCE LLLLULLELLLT BEST ECONOMY MIXTURE PEAK ENDURANCE WITH 2550 LBS MAX GROSS WT tt tT 11141 FEEDS I LT TEILT TT SCARE HH Hl niu XH ENDURANCE WITH 45 MIN RESERYE AT 55 POWER
97. anuals parts catalogs and revisions to both are available from Piper Service Centers or Pipers Customer Services Department Any correspondence regarding the airplane should include the airplane model and serial number to ensure oper response REPORT VB 790 ISSUED JUNE 18 1976 m REVISED JUNE 8 1990 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICL AND MAINTENANCE 28 181 CHEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 8 2 PIPER AIRCRAFT CORPORATION SECTION 8 PA 28 181 CHEROKEE ARCHER II HANDLING SERVICu G AND MAINTENANCE 83 AIRPLANE INSPECTION PERIODS Piper Aircraft Corporation has developed inspection items and required inspection intervals for the PA 28 see PA 28 Service and Inspection Manuals The PA 28 Service Manual contains appropriate forms and all inspection procedures should be complied with by a properly trained knowledgeable and qualified mechanic at authorized Piper Service Center or a reputable repair shop Piper Aircraft Corporation cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards and or not brought into compliance with applicable Service Bulletins issued by Piper Aircraft Corporation instructions issued by the engine propeller or accessory manufacturers or Airworthiness Directives issued by the FAA A Progressive Inspection approved by the Federal Aviation Administr
98. ara 5 5 c Revised fuel quantity figure in para 5 5 g Revised 55 amp 75 range figures in Fig 5 25 Added amp B values to Fig 5 1 Revised weight and balance formula Added Weight Arm and Moment to item 29 a added item 29 b changed existing 29 b to 29 c Revised item 79 Arm and Moment Revised item 115 Dwg 99002 5 to 8 and item 117 Dwg 99003 5 to 7 Revised footnote Revised item 257b Arm and Moment Added info to para 7 25 Revised 10 3 c relocated material to page 10 2 Added relocated material from page 10 1 Rev 2 761 624 PR770120 Ward Evans Jan 20 1977 Corrected to Meteorological Revised NOTE Revised Hot Start procedure Revised 4 13 b Revised Leveling Diagram illustration Revised Dwg Nos of items 287 and 289 Added ELT test info Rev 3 761 624 PR770225 L3 ak Eier Ward Evans Feb 25 1977 REPORT 790 IV PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Revised 8 Number and Pages Description of Revision Code Rev 4 761 624 3 Added new propeller to 1 5 and added footnote PR770712 Revised section 1 21 Conversion Factors FAA Approval Signature and Date Added new propeller to 2 7 item j and added footnote Revised Starting With External Power Source Revised item 4 13 d Starting Engine With External Power Source Added CAU
99. are discussed here this information is not intended to replace such training but only to provide a source of reference and review and to provide information on procedures which are not the same for all aircraft It is suggested that the pilot review standard emergency procedures periodically to remain proficient in them ISSUED JUNE 18 1976 REPORT VB 790 REVISED MARCH 30 1984 3 1 3 PIPER CORPORATION EMERGENCY PROCEDURES 28 181 CHEROKEE ARCHER II UO THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 3 2 PIPER AIRCRAFT CORPP 28 181 CHEROKEE IERII SECTION 3 EMERGENCY PROCEDURES 3 3 EMERGENCY PROCEDURES CHECK LIST ENGINE FIRE DURING START Santer vua crank engine eh d ue Seekers idle cut off Throttle oe een cerrar eut open Electric f elip mp Saas OFF We OFF Abandon if fire continues ENGINE POWER LOSS DURING TAKEOFF 1 runway remains for a normal landing land straight ahead If insufficient runway remains Maintain safe airspeed Make only shallow turn to avoid obstructions Flaps as situation requires If sufficient altitude has been gained to attempt a restart Maintain safe airspeed Fuel selector switch to tank containing fuel Electric fuel pump check
100. arest airport and let a nechanic investigate the problem Watch the oil pressure gauge for an accompanying loss of pressure 123 ALTERNATOR FAILURE Loss of alternator output is detected through zero reading on the ammeter Before executing the ollowing procedure insure that the reading is zero and not merely low by actuating an electrically powered levice such as the landing light If no increase in the ammeter reading is noted alternator failure can be issumed The electrical load should be reduced as much as possible Check the alternator circuit breakers for a opped circuit The next step is to attempt to reset the overvoltage relay This is accomplished by moving the ALT witch to OFF for one second and then to ON If the trouble was caused by a momentary overvoltage condition 16 5 volts and up this procedure should return the ammeter to a normal reading If the ammeter continues to indicate output or if the alternator will not remain reset turn off he ALT switch maintain minimum electrical load and land as soon as practical All electrical load is eing supplied by the battery 25 SPIN RECOVERY Intentional spins are prohibited in this airplane If a spin is inadvertently entered immediately m he throttle to idle and the ailerons to neutral Full rudder should then be applied opposite to the direction of rotation followed by control wheel full orward When the rotation stops neutralize the rudder and ea
101. arness non inertia reel type is installed it must be connected to the seat belt and adjusted to allow proper accessibility to all controls including fuel selector flaps trim etc while maintaining adequate restraint for the occupant If the inertia ree type shoulder harness is installed a pull test of its locking restraint feature should be performed 4 11 BEFORE STARTING ENGINE Before starting the engine the brakes should be set ON and the carburetor heat lever moved to the full COLD position The fuel selector should then be moved to the desired tank 2 790 ISSUED JUNE 18 1976 u m REVISED MARCH 30 1984 PIPER AIRCRAFT CORPORATION SECTION 4 PA 28 181 CHEROKEE ARCHER II NORMAL PROCEDURES 4 13 STARTING ENGINE Starting Engine When Cold Open the throttle lever approximately 1 4 inch Turn the master Switch and the electric fuel pump Move the mixture control to full RICH and engage the starter by rotating the magneto switch clockwise When the engine fires release the magneto switch and move the throttle to the desired setting the engine does not fire within five to ten seconds disengage the Starter prime the engine and repeat the starting procedure b Starting Engine When Hot Open the throttle approximately 1 2 inch Turn ON the master switch and the electric fuel pump Move the mixture control lever to full RICH and engage the starter by rotating the
102. ars bar British Thermal Unit BTU centimeters cm centimeters of mercury at 0 C cm Hg centimeters per second cm sec cubic centimeters cm es feet cu ft cubic feet per minute cu ft min BY 0 4047 43560 0 0015625 76 29 92 1 0133 1 033 14 70 2116 0 98692 14 503768 0 2519958 0 3937 0 032808 0 01316 0 3937 0 1934 27 85 135 95 0 032808 1 9685 0 02237 0 03381 0 06102 3 531 x 10 0 001 2 642 x 107 28317 0 028317 1728 0 037037 7 481 28 32 0 472 0 028317 ISSUED JUNE 18 1976 REVISED JULY 12 1977 TO OBTAIN ha ft Sq mi cm Hg in Hg bar kg cm b sq in Ib sq ft atm Ib sq in kg cal MULTIPLY cubic inches cu in cubic meters m cubic meters per minute m min cubic yards cu yd degrees arc degrees per second deg sec drams fluid dr drams avdp dr avdp feet ft feet per minute ft min BY TO OBTAIN 16 39 5 1 639 x 107 5 787 x 104 cu ft 0 5541 fl oz 0 01639 1 4 329 10 U S gal 0 01732 U S qt 61024 cu 1 308 35 3147 cu ft 264 2 U S gal 35 3147 cu ft min 27 cu ft 0 7646 m 202 U S gal 0 01745 radians 0 01745 radians sec 0 125 fl 0 0625 oz avdp 30 48 cm 0 3048 m 12 in 0 33333 yd 0 0606061 1 894 107 mi 1 645 x 10 NM 0 01136 mph 0 01829 km hr 0 508 cm sec 0 00508 m sec
103. ase proceed toward the nearest airport and be prepared for a forced landing the problem is not a pressure gauge malfunction the engine may stop suddenly Maintain altitude until such time as a dead stick landing can be accomplished Don t change power settings unnecessarily as this may hasten complete power loss Depending on the circumstances it may be advisable to make an off airport landing while power is still available particularly if other indications of actual oil pressure loss such as sudden increases in ter ratures or oil smoke are apparent and an airport is not close If engine stoppage occurs proceed with Power Off Landing ISSUED JUNE 18 1976 REPORT 790 3 9 ECTION 3 PIPERA RAFT CORPORATION MERGENCY PROCEDURES 28 18 ARCHER Il ______ 7 19 LOSS OF FUEL PRESSURE If loss of fuel pressure occurs tum ON the electric fuel pump and check that the fuel selector is on full tank If the problem is not an empty tank Jand as soon as practical and have the engine driven fuel pump nd fuel system checked 21 HIGH OIL TEMPERATURE An abnormally high oil temperature indication may be caused by a low oil level an obstruction in the il cooler damaged or improper baffle seals a defective gauge or other causes Land as soon as practical n appropriate airport and have the cause investigated A steady rapid rise in oil temperature is a sign of trouble Land at the ne
104. at all since it may melt part of the ice which will refreeze in the intake system When using carburetor heat therefore always use full heat and when ice is removed return the control to the full cold position ISSUED JUNE 18 1976 REPORT 790 REVISED MA Y 23 1980 311 SECTION 3 PIPER CORPORATION EMERGENCY PROCEDURES 28 181 ARCHER OOO MM THIS PAGE INTENTIONALLY LEFT BLANK REPORT 790 ISSUED JUNE 18 1976 3 12 SECTION 4 NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page N No 4 1 General asien E 4 1 4 3 Airspeeds For Safe 2 4 1 4 5 Normal Procedures Check 1161 4 3 Prefhght Check 2 etes Ra Rc 4 3 Before Starting Engine es en 4 4 Starting Engine When Cold bae e n do c n OE E cd eed 4 4 Starting Engine When Hot sent ae reden an dees 4 4 Starting Engine When Flooded ee ha hr aaa na 4 4 Starting With External Power Source seuuer hene 4 4 eg e RR UNSERES De 4 4 TAXING rn S WERE NODI 4 4
105. ation FAA is also available to the owner This involves routine and detailed inspections to allow maximum utilization of the airplane Maintenance inspection costs are reduced and the maximum standard of continued airworthiness is maintained Complete details are available from Piper Aircraft Corporation In addition but in conjunction with the above the FAA requires periodic inspections on all aircraft to keep the Airworthiness Certificate in effect The owner is responsible for assuring compliance with these inspection requirements and for maintaining proper documentation in logbooks and or maintenance records spectrographic analysis of the engine oil is available from several sources This inspection if performed properly provides a good check of the internal condition of the engine To be accurate induction air filters must be cleaned or changed regularly and oil samples must be taken and sent in at regular intervals ISSUED JUNE 18 1976 REPORT VB 790 REVISED JUNE 8 1990 8 3 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICING AND MAINTENANCE PA 28 181 CHEROKEE ARCHER II 8 5 PREVENTIVE MAINTENANCE The holder of a pilot certificate issued under Federal Aviation Regulations FAR 61 may perform certain preventive maintenance as defined in the FARs This maintenance may be performed only on an aircraft which the pilot owns and operates and which is not used in air carrier or air taxi commercial operation
106. aution Revised Fig 6 15 Revised item 11 added item 17 Added item 122 moved items 129 and 131 to pg 6 38 1 790 iv c FAA Approval Signature and Date Revision Number and Code Revised D 28 f Pages escription of Revision Rev 8 761 624 Relocated items 129 and 131 from pg 6 37 PR800523 Relocated items 169 thru 177 from pg 6 41 Revised cont items 173 and 175 Moved items 169 thru 177 to pg 6 40 added item 180 relocated item 183 from pg 6 42 Moved item 183 to pg 6 41 Revised para 7 5 Revised para 7 13 Revised para 8 19 Added j Ward Evans May 23 1980 Revised Table of Contents Revised para 1 7 Revised para 1 19 Rev 9 761 624 PR 840330 d dade Unda teda bea dea Revised para 2 1 Revised para 2 7 Revised Table of Contents Revised para 3 1 Revised Table of Contents Revised para 4 5 Qu hye San Added Note Added Note Revised para 4 29 Move para 4 31 from 4 14 Revised para 6 1 Revised para 6 3 Revised para 6 5 Revised Fig 6 5 Revised Fig 6 7 1 saw 2c 1 Revised para 6 9 Added Caution Revised para 7 31 Revised para 8 3 Revised para 8 5 Revised para 8 21 Added new page Revised Sec 3a Revised Table of Contents Chang
107. cate a point on the C G range and weight graph Figure 6 15 If the point falls within the C G envelope the loading meets the weight anc balance requirements Moment In Lbs Basic Empty Weight Pilot and Front Passenger Passengers Rear Seats Fuel 48 Gallon Maximum Baggage Total Loaded Airplane The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point on the range and weight graph Since this point falls within the weight G envelope this loading meets the weight and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THI AIRPLANE IS LOADED PROPERLY Utility Category Operation No baggage or rear passengers allowed SAMPLE LOADING PROBLEM NORMAL CATEGORY Figure 6 9 REPORT VB 7 ISSUED JUNE 18 1976 61 6 PIPER AIRCRAFT CORPORATION GHT AND BALANCE PA 28 181 CHEROKEE ARCHER II Arm Aft Datum Inches Moment In Lbs Basic Empty Weight Pilot and Front Passenger Passengers Rear Seats Fuel 48 Gallon Maximum Total Loaded Airplane 15 must be within approved weight and limits It is the responsibility of the airplane owner and the to insure that the airplane is loaded properly The Basic Empty Weight C G is noted on the Weight Balance Data Form Figure 6 5 If the airplane has been altered refer to the Weight and Bala
108. ce OFF Best angle flaps up 64 KIAS EndXo te samd 87 KIAS TAKEOFF fuel pump ce ue OFF at desired altitude NORMAL e teu or io set duel ve Ee que ees set CRUISING Accelerate to 52 to 65 KIAS Reference performance charts and Avco Lycoming Control wheelie uuu ioa back pressure to rotate to climb attitude SHORT FIELD OBSTACLE CLEARANCE uou tate e 25 second notch Accelerate to 41 to 49 KIAS depending on aircraft weight Control wheel back pressure to rotate to climb attitude After breaking ground accelerate to 45 to 54 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 76 KIAS ISSUED JUNE 18 1976 REVISED MARCH 30 1984 Operator s Manual Normal max 75 Power Arae er set per power table va VE S Re s ANC adjust DESCENT Normal Throttle ule LENT e 2500 rpm Alnspeed cvs 126 KIAS MIXTE Carburetor Heat iv ees cra pre On if required DESCENT Power off Carburetor Heat ois een On if required THO es zu wad me ran Closed required
109. ced 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 the unit has been inadvertently activated for an undetermined time period NOTE If for any reason a test transmission is necessary the test trans mission should be conducted only in the first five minutes of any hour and limited to three audio sweeps If the tests must be made at any other time the tests should be coordinated with the nearest FAA tower or flight service station NARCO ELT 10 OPERATION On the ELT unit itself is a three position switch placarded ON OFF and ARM The ARM position sets the ELT so that it will transmit after impact and will continue to transmit until its battery 15 drained The ARM position is selected when the ELT is installed in the airplane and it should remain in that position To use the ELT as a portable unit in an emergency remove the cover and unlatch the unit from its mounting base The antenna cable is disconnected by a left quarter turn ofthe knurled nut and a pull A sharp tug on the two small wires will break them loose Deploy the self contained antenna by pulling the plastic tab marked PULL FULLY TO EXTEND ANTENNA Move the switch to ON to activate the transmitter In the event the transmitter is activated by an impact it can only be turned off by moving the switch on tl ELT unit to OFF Normal operation can then
110. continues to operate and the air will remain cool for approximately one minute When the throttle is retarded approximately 1 4 inch the clutch will engage and the scoop will extend again supplying cool dry air Optional equipment ISSUED JUNE 18 1976 REPORT VB 790 7 23 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND ATION PA 28 181 CHEROKEE ARCHER II Se ow 7 35 PIPER EXTERNAL POWER An optional starting installation known as Piper External Power PEP is accessible through a receptacle located on the right side of the fuselage aft of the wing An external battery can be connected to the socket thus allowing the operator to crank the engine without having to gain access to the airplane s battery 7 37 EMERGENCY LOCATOR TRANSMITTER The Emergency Locator Transmitter ELT when installed is located in the aft portion of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage This plate is attached with slotted head nylon screws for ease of removal these screws may be readily removed with a variety of common items such as a dime a key knife blade etc If there are no tools available in an emergency the screw heads may be broken off by any means The ELT is an emergency locator transmitter which meet the requirements of FAR 91 52 battery replacement date is marked on the transmitter to comply with FAA regulations the battery must be repla
111. craft Corporation takes a continuing interest in having owners get the most efficient use from their airplane and keeping it in the best mechanical condition Consequently Piper Aircraft from time to time issues service releases including Service Bulletins Service Letters Service Spares Letters and others relating to the airplane Piper Service Bulletins are of special importance and Piper considers compliance mandatory These are sent direcily to the latest FAA registered owners in the United States U S and Piper Service Centers worldwide Depending on the nature of the release material and labor allowances may apply This information is provided to all authorized Piper Service Centers Service Letters deal with product improvements and servicing techniques pertaining to the airplane They are sent to Piper Service Centers and if necessary to the latest FAA registered owners in the U S Owners should give careful attention to Service Letter information Service Spares Letters offer improved parts kits and optional equipment which were not available originally and which may be of interest to the owner Piper Aircraft Corporation offers a subscription service for Service Bulletins Service Letters and Service Spares Leners This service is available to interested persons such as owners pilots and mechanics at a nominal fee and may be obtained through an authorized Piper Service Center or Piper s Customer Services Department Service m
112. d COWINB RR ee secure Inspection covers Nose eco ie rud check Nose gear strut praper inflation 3 25 in A nlets aan seq Ex eck wee ete clear Alternator belt check tension Tow bar and control locks stow neve stowed properly secure Baggage door close and secure Euel strainer Primary flight controls proper operation gs close and secure Required papers on board Seat belts and harness fastened adjust check inertia reel REPORT VB 790 4 3 SECTION 4 NORMAL PROCEDURES 3EFORE STARTING ENGINE Brakes me yy Teest set Carburetor heat full COLD Fuel selector n n n ng desired tank STARTING ENGINE WHEN COLD Throttle entr tm mtr 1 4 open Master switch N Electric fuel pump ON Mixture full RICH Starter engage Throttle trm adjust Oil pressure check If engine does not start within 10 sec prime and repeat starting procedure STARTING ENGINE WHEN HOT THROES 2 e RES RE 1 2 open Master switch ON Electric fuel pump ON Mixturer za PS ee full RICH Starter Throttle 424 2e adj
113. d it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to ensure no air exists in the fuel supply lines 4 Fill with oil to full capacity 5 Place pilot and copilot seats in fourth 4th notch aft of forward position Put flaps in the fully retracted position and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed 6 Weigh the airplane inside a closed building to prevent errors in scale readings due to wind b Leveling 1 With airplane on scales block main gear oleo pistons in the fully extended position 2 Level airplane refer to Figure 6 3 deflating nose wheel tire to center bubble on level REPORT VB 790 ISSUED JUNE 18 1976 6 3 REVISED MARCH 30 1984 SECTION 6 PIPER A RAFT CORPORATION WEIGHT AND BALANCE 28 15 ARCHER U c Weighing Airplane Basic Empty Weight 1 With the airplane level and brakes released record the weight shown on each scale Deduct the tare if any from each reading Scale Net Scale Position and Symbol Reading Tare Weight Left Main Wheel L Basic Empty Weight as Weighed T WEIGHING FORM Figure 6 1 d Basic Empty Weight Center of Gravity 1 The following geometry applies to the PA 28 181 airplane when it is level Refer to Leveling paragraph 6 3 b Level Points Fuselage The datum is 78 4 inches a
114. d or the minimum steady flight speed at which the airplane is controllable Vso Stalling Speed or the minimum steady flight speed at which the _ airplane is controllable in the landing configuration Vx Best Angle of Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance Vy Best Rate of Climb Speed is the airspeed which delivers the ISSUED JUNE 18 1976 greatest gain in altitude in the shortest possible time REPORT VB 790 1 5 SECTION 1 GENERAL OO b Meteorological Terminology ISA OAT Indicated Pressure Altitude Pressure Altitude Station Pressure Wind REPORT VB 790 1 6 PIPERA RAFT CORPORATION 28 18 ARCHER International Standard Atmosphere in which The air is a dry perfect gas The temperature at sea level is 15 Celsius 59 Fahrenheit The pressure at sea level is 29 92 inches hg 1013 2 mb The temperature gradient from sea level to the altitude at which the temperature is 56 5 C 69 7 0 00198 C 0 003564 per foot and zero above that altitude Outside Air Temperature is the air static temperature obtained either from inflight temperature indications or ground meteorological sources adjusted for instrument error compressibility effects The number actually read from altimeter when the barometric subscale has been set 10 29 92 inches of mercury 10
115. d will continue to transmit until the battery is drained to depletion or until the switch is manually moved to the OFF position The ARM position is selected when the transmitter is installed at the factory and the switch should in that position whenever the unit is installed in the airplane The ON position is provided so the unit be used as a portable transmitter or in the event the automatic feature was not triggered by impact or to periodically test the function of the transmitter Select the OFF position when changing the battery when rearming the unit if it has been activated for any reason or to discontinue transmission NOTE If the switch has been placed in the ON position for any reason the OFF position has to be selected before selecting ARM If ARM is selected directly from the ON position the unit will continue to transmit in the ARM position pilot s remote switch located on the left side panel is provided to allow the transmitter to be controlled from inside the cabin The pilot s remote switch is placarded ON AUTO ARM and OFF RESET The switch is normally left in the AUTO ARM position To turn the transmitter off move the switch momentarily to the OFF RESET position The aircraft master switch must be ON to turn the transmitter OFF To actuate the transmitter for tests or other reasons move the switch upward to the ON position and leave it in that position as long as transmission is desired The unit is equi
116. dicator bulb malfunction is indicated and further investigation should be conductec to flight The above operational check may be performed during flight if an in fight failure is suspected The condenser door light is located to the right of the engine instrument cluster in front of the pilot The door light illuminates when the door is open and is off when the door is closed SECTION 5 PERFORMANCE Operation of the air conditioner will cause slight decreases in cruise speed and range Power from the engine is required to run the compressor and the condenser door when extended causes a slight increase in drag When the air conditioner is turned off there is normally no measurable difference in climb cruise or range performance of the airplane NOTE To insure maximum climb performance the air conditioner must be turned off manually before takeoff to disengage the compressor and retract the condenser door Also the air conditioner must be turned off manually before the landing approach in preparation for a possible go around Although the cruise speed and range are only slightly affected by the air conditioner operation these changes should be considered in preflight planning To be conservative the following figures assume that the compressor is operating continuously while the airplane is airborne This will be the case only extremely hot weather a The decrease in true airspeed is approximately 4 KTS at all power s
117. door Also the air conditioner must be turned OFF manually before the landing approach in preparation for a possible go around b Placards In full view of the pilot in the area of the air conditioner controls when the air conditioner is installed WARNING AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE In full view of the pilot to the right of the engine gauges condenser door light AIR COND DOOR OPEN SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating andbook are necessary for this supplement REPORT VB 790 ISSUED JUNE 18 1976 9 3 PIPER AIRCRAFT CORPORATION SECTION 9 SUPPLEMENTS PA 28 181 CHEROKEE ARCHER SECTION 4 NORMAL PROCEDURES Prior to takeoff the air conditioner should be checked for proper operation as follows a Check aircraft master switch ON b Tum the air conditioner control switch to and the fan switch to one of the operating positions the AIR COND DOOR OPEN warning light will turn on thereby indicating proper air conditioner condenser door actuation c Turn the air conditioner control switch to OFF the AIR COND DOOR OPEN warning light will go out thereby indicating the air conditioner condenser door is in the up position d If the AIR COND DOOR light does not respond as specified above an air conditioner system or in
118. e disengage the lock and pull the mixture control until the engine becomes rough indicating that the lean mixture limit has been reached in the leaner cylinders Then enrich the mixture by pushing the control towards the instrument panel until engine operation becomes smooth If the airplane is equipped with the optional exhaust gas temperature EGT gauge a more accurate means of leaning is available to the pilot For this procedure refer to the Avco Lycoming Operator s Manual Always remember that the electric fuel pump should be turned ON before switching tanks and should be left on for a short period thereafter In order to keep the airplane in best lateral trim during cruising flight the fuel should be used alternately from each tank It is recommended that one tank be used for one hour after takeoff then the other tank be used for two hours then return to the first tank which will have approximately one and one half hours of fuel remaining if the tanks were full at takeoff The sernnd tank will contain approximately one half hour of fuel Do not run tanks completely dry in flight lectric fuel pump should be normally 5 that any malfunction of the engine driven fuel pump is apparent If signs of fuel starvation should occur at any time during flight fuel exhaustion should be suspected at which time the fuel selector should be immediately positioned to the other tank and the electric fuel pump
119. e carried in the aircraft at all times 1 Pilot s Operating Handbook 2 Weight and Balance data plus a copy of the latest Repair and Alteration Form FAA 337 if applicable 3 Aircraft equipment list Although the aircraft and engine logbooks are not required to be in the aircraft they should be made available upon request Logbooks should be complete and up to date Good records will reduce maintenance cost by giving the mechanic information about what has has not been accomplished ISSUED JUNE 18 1976 REPORT SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICIN AND MAINTENANCE PA 28 181 CHEROKEE ARCHER II 8 9 GROUND HANDLING 2 b REPORT 790 8 6 Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed below the forward ledge of the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly Towing lugs are incorporated as part of the nose gear fork CAUTION When towing with power equipment not tum the nose gear beyond its steering radius in either direction as this will result in damage to the nose gear and steering mechanism CAUTION Do not tow the airplane when the controls are secured In the event towing lines are necessary Topes should be attached to both main gear struts as high up on the t
120. e refueling must not exceed 15 by volume of the refueled quantity and to ensure its effectiveness must be blended at not less than 10 by volume One and one half liquid ozs per ten gallons of fuel would fall within this range A blender supplied by the additive manufacturer should be used Except for the information contained in this section the manufacturer s mixing or blending instructions should be carefully followed CAUTIONS Assure that the additive is directed into the flowing fuel Stream The additive flow should start after the stop before the fuel flow Do permit the concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the fuel tanks Some fuels have anti icing additives preblended in the fuel at the refinery so no further blending should be performed REPORT VB 790 ISSUED MARCH 30 1984 3 11a REVISED JUNE 8 1990 PIPER AIRCRAFT CORPORATION SECTION 8 28 181 HANDLING SERVICING 2 MAINTENANCE c Filling Fuel Tanks Observe all required precautions for handling gasoline Fuel is stored in two twenty five gallon 24 gal usable tanks There is approximately 17 gallons in the fuel tank when fuel level is even with bottom of filler neck indicator ISSUED MARCH 30 1984 REPORT PIPER AIRCRAFT CORPORATION SECTION 8 HANDLING SERVICIN MAINTENANCE 28 184 CHEROKEE ARCHER II FUEL DRAIN
121. e reverse order of removal 8 13 BRAKE SERVICE The brake system is filled with MIL H 5606 petroleum base hydraulic brake fluid The fluid level should be checked periodically or at every 50 hour inspection and replenished when necessary The brake reservoir is located on the fire wall in the engine compartment If the entire system must be refilled fill with fluid under pressure from the brake end of the system This will eliminate air from the system No adjustment of the brake clearances is necessary If after extended service brake blocks become excessively worn they should be replaced with new segments REPORT 790 ISSUED JUNE 18 1976 8 8 SECTION 8 HANDLING SERVICIN AND MAINTENANCE PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER II t uaganu 1 437 5 101409 LH9 H 5 10 1902 Alawassy 1708 SlA312 7 NOLLNE 3Sv313H 1437 BAQNINAD 1437 LHOIY 5 8 9 Figure 8 1 REPORT VB 790 BRAKE SYSTEM ISSUED JUNE 18 1976 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICIN AND MAINTENANCE PA 28 181 CHEROKEE ARCHER II
122. e to the stalling speed After ground contact hold the nose wheel off as long as possible As the airplane slows down gently lower the nose and apply the brakes Braking is most effective when flaps are raised and back pressure is applied to the control wheel putting most of the aircraft weight on the main wheels In high wind conditions panicularly in strong crosswinds it may be desirable to approach the ground at higher than normal speeds with partial or no flaps ISSUED JUNE 18 1976 REPORT VB 790 REVISED MARCH 30 1984 414 PIPER AIRCRAFT CORI ATION SECTION 4 PA 28 181 CHEROKEE AKCHER II NORMAL PROCEDURES 4 31 STOPPING ENGINE At the pilot s discretion the flaps should be raised and the electric fuel pump turned OFF NOTE The flaps must be placed in the UP position for the flap step to support weight Passengers should be cautioned accordingly The air conditioner and radios should be turned OFF and the engine stopped by disengaging the mixture control lock and pulling the mixture contro back to idle cut off The throttle should be left full aft to avoid engine vibration while Stopping Then the magneto and master switches must turned OFF PARKING lf necessary the airplane should be moved on the Bround with the aid of the nose wheel tow bar provided with each airplane and secured behind the rear seats The aileron and stabilator controls should be secured by looping the safety belt through the control w
123. eceiver Cert Basis TSO C36c C40a C66c C34c 3 3 58 6 193 7 Narco Nav 114 Receiver Cert Basis TSO C38b 40 C36c C34c 2 5 57 4 144 9 Narco Nav 121 Receiver a Single Ad 58 4 181 b Dual 6 2 58 4 362 Cert Basis TSO C36c C40c C66a 1 Narco 122 Receiver a Single cr 99 4 507 b Dual Eme 8 6 82 9 713 Cert Basis TSO C35d C36c C40c 3 Narco Nav 1224 Receiver a Single 5 2 98 5 512 b Dual 8 8 82 2 723 Cert Basis TSO C34c C35d C36c C40c Narco Nav 124A Receiver vi a Single 6 2 92 3 512 b Dual er 10 9 7342 841 Basis TSO C35d C36c C40a ight includes marker antenna and cable PORT VB 790 ISSUED JUNE 18 1976 6 REVISED JULY 12 1977 PIPER AIRCRAFT CORPORATION SECTION 6 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE m Radio Equipment Optional Equipment cont Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In 247 Narco ID 124 VOR LOC GS Indicator a Single 1 2 60 5 73 b Dual De 2 4 60 5 145 Cert Basis TSO C34c C35d C36c C40c 249 Narco UGR 2A Glide Slope a Single 4 2 154 0 647 b Dual EUN 8 4 220 0 1848 Cert Basis TSO C34b 251 Narco UGR 3 Glide Slope Cert Basis TC 2A13 4 2 154 0 647 253 Narco MBT 12 R Marker Beacon Cert Basis TC 2A13 3 1 69 1 2
124. eceiver controls are located on the left side of the front panel 1 through 4 The SENS button 4 selects either high or low sensitivity as indicated by the HI or LO LED being lit Low sensitivity is used on ILS approaches while high sensitivity allows operation over airway markers or to get an earlier indication of nearing the outer marker during an approach The marker audio is selected initially by pressing the MKR MUTE button 2 If no marker beacon signal is being received then pressing again will deselect the marker audio This operation is similar to selecting any other source on the GMA 340 However if the second button press occurs while a marker beacon signal is being received then the marker audio is muted but not deselected The button s LED will remain lit to indicate that the source is still selected The 340 s SmartMute function then monitors the marker signal and automatically unmutes the audio when the current marker signal is no longer being received In all cases the marker beacon lamps operate independently of any audio selection and cannot be turned off 8 AIRPLANE HANDLING CARE AND MAINTENANCE No change AFM M10 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M12 GI 106A EASA APPROVED FLIGHT MANUAL SUPPLEMENT CDI GI 106A This document must be carried in the aircraft at all times It describes the operating procedures for the GI 106A when it has been installed in acc
125. ed Sec Title 4 Ware Gian Ward Evans March 30 1984 REPORT VB 790 iv d PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision FAA Approval Number and Revised Description of Revision Signature and Code Date Rev 10 761 624 Moved item c to pg 1 4 PR900608 Relocated item c from 1 3 Revised item c Revised para 8 1 Revised para 8 3 Revised para 8 5 Revised para 8 19 Added Note 5 Revised Fuel Grade Comparison Chart D H Trompler Revised Emergency Operation Item a 2 July 30 1990 REPORT 790 iv e SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 OPERATING TIPS REPORT VB 790 v SECTION 1 GENERAL SECTION 1 GENERAL 1 GENERAL Paragraph Page No No 1 Intteduetlon do et ore ASD een 1 1 1 5 me n SEN RR PR 8 s E FA 1 3 1 5 e ere ee 1 3 1 7 WS ee 1 3 1 9 BY Ge HEA TE 1 3 1 4 113 Standard Airplane W
126. ed at either control wheel c An autopilot runaway with a 3 second delay in the initiation of while operating in a climb cruise or descending flight could result in a 45 bank and 180 altitude loss Maximum altitude loss measured at 149 KIAS ina descent d An autpilot runaway with a 1 second delay in the initiation of during an approach operation coupled or uncoupled could result in a 18 bank and 10 altitude loss SECTION 4 NORMAL PROCEDURES PREFLIGHT 8 AUTOPILOT 1 Place Radio Coupler in HDG Mode Gf installed and place the AP ON OFE switch to the ON position to engage roll section Rotate roll command knob left and right and observe that control wheel describes a corresponding left and right tum then center knob 2 Set correct compass heading on D G and um HDG bug to aircraft heading Engage mode rocker switch and rotate HDG bug left and right Aircraft control wheel should tum same direction as bug Grasp control wheel and manually override servo both directions REPORT VB 790 ISSUED JUNE 18 1976 REVISED JUNE 8 1990 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 181 CHEROKEE ARCHER II b RADIO COUPLER OPTIONAL 1 Tune and identify VOR or VOT station Position Radio Coupler to OMNI Mode Engage Autopilot ROLL and HDG switches Set HDG bug to aircraft heading and rotate O B S
127. ed position The flaps must be placed in the UP position before they will lock and support weight on the step Before attempting to reset any circuit breaker allow a two to five minute cooling off period Before starting the engine check that all radio switches light switches and the pitot heat switch are in the off position so as not to create an overloaded condition when the starter is engaged Strobe lights should not be operating when flying through overcast and clouds since reflected light can produce spacial disorientation Do not operate strobe lights when taxiing in the vicinity of other aircraft The rudder pedals are suspended from a torque tube which extends across the fuselage The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes In an effort to avoid accidents pilots should obtain and study the safety related information made available in FAA publications such as regulations advisory circulars Aviation News and safety aids The shape of the wing fuel tanks is such that in certain maneuvers the fuel may move away from the tank outlet If the outlet is uncovered the fuel flow will be interrupted and a temporary loss of power may result Pilots can prevent inadvertent uncovering of the outlet by avoiding maneuvers which could result in uncovering the outlet R
128. edals and a hand lever and master cylinder located below and behind the left center of the instrument sub panel The toe brakes and the hand brake have their own brake cylinders but they share a common reservoir The brake fluid reservoir is installed on the top left front face of the fire wall The parking brake is incorporated in the master cylinder and is actuated by pulling back on the brake lever depressing the knob attached to the left side of the handle and releasing the brake lever To release the parking brake pull back on the brake lever to disengage the catch mechanism and allow the handle to swing forward refer to Figure 7 5 ISSUED JUNE 18 1976 REPORT VB 790 7 3 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND Orc RATION PA 28 181 CHEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK REPORT 790 ISSUED JUNE 18 1976 74 SECTION 7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER II FLIGHT CONTROL CONSOLE Figure 7 3 7 9 FLIGHT CONTROLS Dual controls are provided as standard equipment with a cable system used between the controls and the surfaces The horizontal tail stabilator is of the all movable slab type with a trim tab mounted on the trailing edge of the stabilator to reduce the control system forces This tab is actuated by a control wheel on the floor between the front seats Figure 7 3 rudder trim adjustment is mounted on the right side of the p
129. edestal below the throttle quadrant and permits directional trim as needed in flight refer to Figure 7 5 The flaps are manually operated and springloaded to return to the up position A past center lock corpor ted in the actuating linkage holds the when it is in the up position so that it may be used as step on the right side The flap will not support a step load except when in the full up position so it must be completely retracted when used as a step The flaps have three extended positions 10 25 and 40 degrees REPORT VB 790 ISSUED JUNE 18 1976 7 5 PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION AND OPERATION 28 181 CHEROKEE ARCHER II ye 7 11 ENGINE CONTROLS Engine controls consist of a throttle control and a mixture control lever These controls are located on the control quadrant on the lower center of the instrument panel Figure 7 5 where they are accessible to both the pilot and the copilot The controls utilize teflon lined control cables to reduce friction and binding The throttle lever is used to adjust engine RPM The mixture control lever is used to adjust the air to fuel ratio The engine is shut down by the placing of the mixture control lever in the full lean position In addition the mixture control has a lock to prevent inadvertent activation of the mixture control For information on the leaning procedure see the Avco Lycoming Operator s Manual The friction adjustment
130. ee THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 4 2 PIPER AIRCRAFT CORPO ION 28 181 CHEROKEE AR ILI SECTION 4 NORMAL PROCEDURES e96 6 TTT D WALK AROUND Figure 4 1 4 5 NORMAL PROCEDURES CHECK LIST PREFLIGHT Control wheel release belts Master switch ON Fuel quantity gauges Master switch OFF TgnitiOn3 ids nuce e wid c RO OFF oz tae y s check for damage Control surfaces check for interference free of ice snow frost Hl wa check for interference diets Son an OE a free of ice snow frost Stall WaInlng esca anne check Navigation 5 check Fuel tanks cause desee check supply visually secure caps Fuel tank sumps and check for water sediment and proper fuel Piel verts Wyss open Main gear struts proper inflation 4 50 TURES c ISSUED JUNE 18 1976 REVISED MARCH 30 1984 Brake blocks Pitot head Windshield Propeller and spinner Fuel and oil Dd 4 remove cover holes clear Wise Ed pA X Cox clean check level Bipstick un Sees Aone dre properly seate
131. eed ide dav oad Pr De As required Mixt re deer vede e ees As required Powers ser e az Verify with throttle every 30 seconds REPORT VB 790 4 5 CORPORATION 28 181 ARCHER __ SECTION 4 NORMAL PROCEDURES APPROACH AND LANDING Fuel selector proper tank Seatbacks erect Belts harness essent fasten adjust Electric fuel pump rer rtt ON Mixture ccc cee eee set Flaps cere t m mtn set 102 KIAS max Air conditioner OFF Trim to 75 KIAS Final approach speed flaps 40 66 KIAS STOPPING ENGINE Flaps 22405844 se sere retract Electric fuelpump OFF Air conditioner OFF AGIOS rate OFF FROME coreane tie mim full aft mmt idle cut off Magnetos OFF Masterswitch OFF PARKING Parking brake set Control wheel secured with belts Flaps full up Wheel chocks in place Tie secure REPORT VB 790 4 6 ISSUED JUNE 18 1976 REVISED MARCH 30 1984 PIPER AIRCRAFT CORPOI ION SECTION 4 28 181 CHEROKEE ARCHER II NORMAL PROCEDURES 4 7 AMPLIFIED NORMAL PROCEDURES GENERAL The following paragraphs are provided to supply d
132. eene eee TIS i Ti tt erent LEZI TI 0 40 60 8 90 100 no 120 130 OUTSIDE AIR TEMP TRUE AIRSPEED KNOTS 20 10 0 10 20 30 OUTSIDE AIR TEMP C Ex le pressure altitude 5500 ft Cruise 30 55 True airspeed 97 5 knots SPEED POWER PERFORMANCE CRUISE SERIAL NOS 28 7790001 THROUGH 7790607 Figure 5 19 ISSUED JUNE 18 1976 REPORT VB 790 REVISED JULY 12 1977 5 21 PIPER CRAFT CORPORATION SECTION 5 ARCHER II PERFORMANCE PA 28 1 PA 28 181 SPE a HHHH nan nsere 4 INE HLHEH HHRHRHHRH IF REMOVED 4 LLILLLII I PAT SFR HEHE 20202425252 POLL LLU COCO EEE ACT WZ Aum 20 0 20 40 60 80 100 F 109 10 120 20 0 20 40 C TRUE AIR SPEED KTS QUT
133. eights 1 4 115 SDAS acea we che oe 1 4 117 ues se me me 1 4 1 19 Symbols Abbreviations and TORO ca exe em i e RE ce 1 5 1 21 eo ke so EG em WG TA Se ae cc ce 1 11 790 14 PIPER AIRCRAFT CORP TION SECTION 1 28 181 CHEROKEE II GENERAL SECTION 1 GENERAL 1 1 INTRODUCTION This Pilot s Operating Handbook is designed for maximum utilization as an operating guide for the pilot includes the material required to be furnished to the pilot by C A R 3 and FAR Part 21 Subpart J It also contains supplemental data supplied by the airplane manufacturer his handbook is not designed as a substitute for adequate and competent flight instruction knowledge of current airworthiness directives applicable federal air regulations or advisory circulars It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status Assurance that the airplane is in an airworthy condition is the responsibility of the owner The pilot in command is responsible for determining that the airplane is safe for flight The pilot is also responsible f
134. el to Descend 0000007 5 30 aie SS fk BS T ered nce 5 3 5 32 I E 5 33 ISSUED JUNE 18 1976 REPORT VB 790 REVISED JULY 12 1977 5 9 5 PIPER RAFT CORPORATION ERFORMANCE 28 181 CHEROKEE ARCHER II Fe nn THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 5 10 PIPER AIRCRAFT CORPL TION SECTION 5 28 181 CHEROKEE ARCHER I PERFORMANCE EE Rcg PA 28 181 AIRSPEED SYSTEM CALIBRATION 2550 LBS GROSS WEIGHT ET E EEE T CALIBRATED AIRSPEED KNOTS 0 90 100 110 120 130 140 150 160 170 KIAS NO INSTRUMENT ERROR 40 0 50 70 AIRSPEED SYSTEM CALIBRATION Figure 5 REPORT VB 790 ISSUED JUNE 18 1976 ap 1 SECTION 5 PIPER CORPORATION ERFORMANCE 28 15 CHEROKEE ARCHER II 28 181 POWER OFF 0 FLAPS 25 FLAPS 40 FLAPS p 22 20 B 25 24 22 20 18 40 WEIGHT 100 LBS ANGLE OF BANK DEGREES xample Gross weight 2300 lbs Angle of bank 20 Flap position 25 Stall speed 46 knots indicated airspeed INDICATED AIRSPEED NO INDICATOR ERROR STALL SPEEDS Figure 5 3 60 SLONY 0334 TIVAS REPORT VB 790 ISSUED JUNE 18 1976 12 PIPER AIRCRAFT CORPO SECTION 5
135. elected using the frequency select knobs The selected STANDBY frequency is put into the ACTIVE frequency windows by pressing the frequency transfer button Either the standby frequency the flight timer or the elapsed timer is displayed in this position The flight timer and elapsed timer are displayed replacing the standby frequency which goes into blind memory to be called AFM M26 29 2005 Diamond 10 11 AFM M26 MAINTENANCE Doc No AFM M26 KR87 back at any time by depressing the FRQ button Flight time or elapsed time are displayed and annunciated alternatively by depressing the FLT ET button FLIGHT TIMER AND ELAPSED TIMER MODE ANNUNCIATION Either the elapsed time ET or flight time FLT mode is annunciated here FREQUENCY SELECT KNOBS Selects the standby frequency when FRQ is displayed and directly selects the active frequency whenever either of the time function is selected The frequency selector knobs may be rotated either clockwise or counterclockwise The small knob is pulled out to tune the 1 s The small knob is pushed in to tune the 10 s The outer knob tunes the 100 s with rollover into the 1000 s up to 1799 These knobs are also used to set the desired time when the elapsed timer is used in the countdown mode ON OFF VOLUME CONTROL SWITCH ON OFF VOL Controls primary power and audio output level Clockwise rotation from OFF position applies primary power to the receiv
136. enehmigt Datum 7 Juni 02 Ausgabe 1 28 169 Falls aus unbekannten Gr nden der Krafistoffvorrat im rechten Tank weiniger als sein sollte kann ausnahmsweise die Landung mit dem linken Tank ausgef hrt werden Seite 2von2 vom 24 10 2001
137. eoff and landing was actually demonstrated during certification tests The distance required to accelerate an airplane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the airplane to a stop A part of a route Each end of that part is identified by 1 a geographical location or 2 a point at which a definite radio fix can be established REPORT VB 790 1 7 SECTION 1 GENERAL MEN Reference Datum Station Ann Moment Center of Gravity C G Limits Usable Fuel Unusable Fuel Standard Empty Weight Basic Empty Weight Payload Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight REPORT VB 790 1 8 PIPER AIP RAFT CORPORATION 28 18 JEROKEE ARCHER f Weight and Balance Terminology An imaginary vertical plane from which all horizontal distances are measured for balance purposes A location along the airplane fuselage usually given in terms of distance from the reference datum The horizontal distance from the reference datum to the center of gravity C G of an item The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify balance calculations by reducing the number of digits The point at which an airplane would balance if suspended Its distance from the reference datum is found by dividin
138. er further clockwise rotation increases audio level Audio muting causes the audio output to be muted unless the receiver is locked on a valid station SET RESET ELAPSED TIMER BUTTON SET RST The set reset button when pressed resets the elapsed timer whether it is being displayed or not FLIGHT TIMER ELAPSED TIMER MODE SELECTOR BUTTON FLT ET The Flight Timer Elapsed Time mode selector button when pressed alternatively selects either Flight Timer mode or Elapsed Timer mode FREQUENCY TRANSFER BUTTON FRQ The FRQ transfer button when pressed exchanges the active and standby frequencies The new frequency becomes active and the former active frequency goes into standby BFO Beat Frequency Oscillator BUTTON The BFO button selects the BFO mode when in the depressed position See note under item 3 lt Diamond MAINTENANCE Doc No AFM M26 KR87 12 ADF BUTTON The ADF button selects either the ANT mode the ADF mode The ANT mode is selected with the ADF button in the out position The ADF mode is selected with the ADF button in the depressed position 13 LUBBER LINE Indicates magnetic heading of the airplane 14 COMPASS CARD Slaved Compass Card derives its heading input from the Slaved Compass System KCS 55A 15 BEARING POINTER Indicates magnetic bearing to the station 16 SYNC KNOB The compass card is synchronized to the HSI compass card by rotating the SYNC knob until the heading matches that o
139. etailed information and explanations of the normal procedures necessary for the safe operation of the airplane 4 9 PREFLIGHT CHECK The airplane should be given a thorough preflight and walk around check The preflight should include a check of the airplane s operational status computation of weight and C G limits takeoff distance and in flight performance A weather briefing should be obtained for the intended flight path and any other factors relating to a safe flight should be checked before takeoff CAUTION The flap position should be noted before boarding the aircraft The flaps must be placed in the position before they will lock and support weight on the step Upon entering the cockpit release the seat belts securing the control wheel Turn the master switch and check the fuel quantity gauges for sufficient fuel After the fuel quantity check is made turn the master switch and check that the ignition switch is OFF To begin the exterior walk around check for external damage and operational interference of the control surfaces or hinges Insure that the wings and control surfaces are free of snow ice frost or any other foreign materials operational check of the stall warning system and navigation lights should now be made Turn the master switch ON Lift the detector while checking to determine if the horn is actuated and check that the navigation lights are illuminated The mas
140. ettings b The decrease in range may be as much as 32 nautical miles for the 48 gallon capacity REPORT VB 790 ISSUED JUNE 18 1976 94 PIPER AIRCRAFT CORPORATION SECTION 9 PA 28 181 CHEROKEE ARCHER II SUPPLEMENTS The climb performance is not compromised measurably with the air conditioner operating since the compressor is declutched and the condenser door is retracted both automatically when a full throttle position is selected When the full throttle position is not used or in the event of a malfunction which would cause the compressor to operate and the condenser door to be extended a decrease in rate of climb of as much as 100 fpm can be expected Should a malfunction occur which prevents condenser door retraction when the compressor is turned off a decrease in rate of climb of as much as 50 fpm can be expected 2 ISSUED JUNE 18 1976 ie 5 PIPER AIRCRAFT CORPORATION SECTION 9 SUPPLEMENTS PA 28 181 CHEROKEE ARCHER ln sn THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 7 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 28 181 CHEROKEE ARCHER II SUPPLEMENTS SUPPLEMENT 2 AUTOFLITE II AUTOPILOT INSTALLATION SECTION 1 GENERAL x This supplement supplies information necessary for the operation of the airplane when the optional AutoFlite II Autopilot is installed The information contained within this supplement is to be used as described in conjunct
141. eviation bar provides the pilot with vertical steering information during ILS approaches The glideslope circuitry is energized when the associated localizer frequency is selected on the navigation receiver Observe that the glideslope warning flag is concealed The glideslope deviation bar deflects towards the direction the pilot must fly to remain on the glide path AFM M12 Rev 06 Feb 2006 lt Diamond MAINTENANCE Doc No AFM M12 GI 106A If the glideslope deviation bar deflects upward the airplane is below the glide path and the pilot must climb to again intercept the glide path and center the deviation bar If the deviation bar deflects downward the airplane is above the glide path and the pilot must descend to again intercept the glide path and center the deviation bar When the deviation bar is centered the airplane is on the glide path 8 AIRPLANE HANDLING CARE AND MAINTENANCE No change AFM M12 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M26 KR87 EASA APPROVED FLIGHT MANUAL SUPPLEMENT KR87 This document must be carried in the aircraft at all times It describes the operating procedures for the KR87 when it has been installed in accordance with the KR87 installation manual and EODM 101 For aircraft with EASA Approved Airplane Flight Manual this document serves as the EASA Approved Flight Manual Supplement for the KR87 For aircraft that do not have an approved flight manual th
142. f altitude permits switch the fuel selector to another tank containing fuel and turn the electric fuel pump ON Move the mixture control to RICH and the carburetor heat to ON Check the engine gauges for an indication of the cause of the power loss Check to insure the primer is locked 1f no fuel pressure is indicated check the tank selector position to be sure it is on a tank containing fuel When power is restored move the carburetor heat to the OFF position and tum OFF the electric fuel pump lf the preceding steps do not restore power prepare for an emergency landing If time permits tum the ignition switch to L then to then back to BOTH Move the throttle and mixture control levers to different settings This may restore power if the problem is too rich or too lean a mixture or if there is a partial fuel system restriction Try other fuel tanks Water in the fue could take some time to be used up and allowing the engine to windmill may restore power If power is due to _ water fuel pressure indications will be normal If engine failure was caused by fuel exhaustion power will not be restored after switching fuel tanks until the empty fuel lines are filled This may require up to ten seconds If power is not regained proceed with the Power Landing procedure refer to the emergency check list and paragraph 3 13 3 13 POWER OFF LANDING If loss of power occurs at altitude trim the aircraft
143. f the HSI OPERATING THE KR 87 TURN ON Rotate the ON OFF VOL knob clockwise from the detented OFF position The unit will be activated and will be ready to operate Rotation of this control also adjusts audio volume The KR 87 has audio muting which causes the audio output to be muted unless the receiver is locked on a valid station FREQUENCY SELECTION The active frequency to which the ADF is tuned is displayed in the left side of the window at all times standby frequency is displayed in the right side when is annunciated The standby frequency is placed in blind memory when either FLT Flight Time or ET Elapsed Time mode is selected With FRQ annunciated the standby frequency is selected using the frequency select knobs which may be rotated either clockwise or counterclockwise Pull the AFM M26 Rev 29 Nov 2005 Diamond MAINTENANCE Doc No AFM M26 KR87 small inner knob out to tune 1 s Push the smaller inner knob to tune 10 s The outer knob tunes the 100 s and the 1000 s up to 1799 The standby frequency selected may then be put into the active window by pressing the FRQ button The standby and active frequencies will be exchanged flip flopped the new frequency will become active and the former active frequency will go into standby OPERATING MODES Antenna ANT mode is selected and annunciated when the ADF button is in the out position ANT provides improved audio rece
144. f the page opposite the page number will indicate that an entire page was added Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations Changes in capitalization spelling punctuation or the physical location of material on vage will not be identified by symbols ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below Title ii through v 1 1 through 1 14 2 1 through 2 8 3 1 through 3 12 4 1 through 4 16 5 1 through 5 28 6 1 through 6 52 7 1 through 7 26 8 1 through 8 16 9 1 through 9 14 10 1 through 10 2 iij PILOT S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA 28 181 Cherokee Archer II Pilot s Operating Handbook REPORT VB 790 issued June 18 1976 Revision Revised Approval Number and Pages Description of Revision Signature and Code Date 2 1 Revised Never Exceed Speed KIAS value Rev 1 761 624 PR760804 Revised Airspeed Indicator Markings Revised report number at bottom of page Revised Arm and Moment for item 177 Revised items 193 195 and 197 Wert Er Ward Evans August 4 1 Revised Open Door procedure Revised para 3 27 info Added Caution to para 4 9 relocated material to page 4 8 Added relocated material from page 4 7 Added Note to para 4 31 Revised stall speed in para 4 35 Revised wording in p
145. ficient This section provides information in th one or more of the various optional systems and equipment operation of the airplane when equipped wi not provided with the standard airplane of the Supplements provided by this section are Approved and consecutively numbered as a permanent part of this Handbook The information contained in each Supplement applies only when the related equipment is installed in the airplane ISSUED JUNE 18 1976 REPORT VB 790 9 1 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS 28 181 CHEROKEE ARCHER ain THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 9 2 PIPER AIRCRAFT CORPORATION SECTION 9 28 181 CHEROKEE ARCHER II SUPPLEMENTS SUPPLEMENT 1 AIR CONDITIONING INSTALLATION SECTION 1 GENERAL 3 This supplement supplies information necessary for the efficient operation of the airplane when optional air conditioning system is installed The information contained within this supplement is to be used described in conjunction with the complete 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 air conditioning system is installed SECTION 2 LIMITATIONS To insure maximum climb performance the air conditioner must be turned OFF manually prior to takeoff to disengage the compressor and retract the condenser
146. for best gliding angle 76 KIAS Air Cond off and look for a suitable field If measures taken to restore power are not effective and if time permits check your charts for airports in the immediate vicinity it may be possible to land at one if you have sufficient altitude If possible notify the FAA by radio of your difficulty and intentions If another pilot or passenger is aboard let him help When you have located a suitable field establish a spiral 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 easily be reached slow to 66 KIAS with flaps down for the shortest landing Excess altitude may widening your pattern using flaps or slipping or a combination of these Touchdown should normally be made at the lowest possible airspeed When committed to a landing close the throttle control and shut OFF the master and ignition switches Flaps may be used as desired Turn the fuel selector valve to OFF and move the mixture to idle cut off The seat belts and shoulder hamess if installed should be tightened Touchdown should be normally made at the lowest possible airspeed REPORT VB 790 ISSUED JUNE 18 1976 3 8 PIPER AIRCRAFT CORPO ION SECTION 3 PA 28 181 CHEROKEE ARCHER II EMERGENCY PROCEDURES 3 15 FIREIN FLIGHT The
147. fuel in the system may be drained through the filter bowl Any individual tank may be drained by closing the selector valve and then draining the desired tank 8 23 TIREINFLATION For maximum service from the tires keep them inflated to the proper pressures 18 psi for the nose gear and 24 psi for the main gear All wheels and tires are balanced before original installation and the relationship of tire tube and wheel should be maintained upon reinstallation Unbalanced wheels can cause xtreme vibration in the landing gear therefore in the installation of new components it may be necessary to rebalance the wheels with the tires mounted When checking tire pressure examine the tires for wear 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 The battery box has a plastic tube which is normally closed off with a cap and which should be opened occasionally to drain off any accumulation of liquid The battery should be checked for proper fluid level DO NOT fill the battery above the baffle plates DO NOT fill the battery with acid use water only hydrometer check will determine the percent of charge in the battery If the battery is not up to charge recharge starting at a 4 amp rate and finishing with a 2 amp rate Quick charges are not recommended 8 27 CLEANING Cleaning Engine Compartment Before cleaning the engine c
148. g m atm cm Hg in Hg kg m 1 cu in deg arc rev deg sec rev sec pm radians radians sec radians sec PIPER A 2AFT CORPORATION 28 181 ARCHER pM MULTIPLY rod slug square centimeters cm square feet sq ft square inches sq in square kilometers km square meters m square miles sq mi square rods sq rods square yards sq yd yards yd 32 174 0 1550 0 001076 929 0 092903 144 0 1111 2 296 x 107 6 4516 6 944 x 10 0 3861 10 76391 1 196 0 0001 2 590 640 30 25 0 8361 9 0 0330579 0 9144 3 36 0 181818 TO OBTAIN ft yd Ib in sq ft cm m 2 54 in sq yd acres cm sq ft q mi sq ft sq yd ha km acres sq yd m sq ft sq rods m ft in rod ISSUED JUNE 18 1976 REVISED JULY 12 1977 SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page No No 231 General DIL NIS A enciende vt eftt ES 2 1 2 Airspeed Limitations e i ie EE reu deals 2 1 2 5 Airspeed Indicator Markings D 2 2 2 7 Power Plant Limitations uere Wow wah rcr DES Uu IR DAE I 2 2 2 9 Power Plant Instrument 2 3 2 11
149. g the PEP jumper cables the master switch should be OFF but it is possible to use the ship s battery in parallel by turning the master switch ON This will give longer cranking capabilities but will not increase the am perage REPORT VB 790 ISSUED JUNE 18 1976 49 REVISED JULY 3 1978 PIPER _ CORPORATION SECTION 4 NORMAL PROCEDURES 28 181 CHEROKEE ARCHER II CAUTION Care should be exercised because if the ship s battery has been depleted the external power supply can be reduced to the level of the ship s battery This can be tested by turning the master switch ON momentarily while the starter is engaged If cranking speed _ increases the ship s battery is at a higher level than the external power supply REPORT 790 ISSUED JUNE 18 1976 REVISED JULY 12 1977 4 10 PIPER AIRCRAFT _ SECTION 4 PA 28 181 CHEROKEE ARCHER II NORMAL PROCEDURES 4 15 WARM UP Warm up the engine 800 to 1200 RPM for not than two minutes in warm weather and four minutes in cold Avoid prolonged idling at low RPM as this practice result in fouled spark plugs Takeoff may be made as soon as the ground check is completed provided that the throttle may be opened fully without backfiring or skipping and without a reduction in engine oil pressure Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones gravel or an
150. g the total moment by the total weight of the 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 a given weight Fuel available for flight planning Fuel remaining after a runout test has been completed in accordance with governmental regulations Weight of a standard airplane including unusable fuel full operating fluids and full oil Standard empty weight plus optional equipment Weight of occupants cargo and baggage Difference between takeoff weight or ramp weight if applicable and basic empty weight Maximum weight approved for ground maneuver dt incl weight of start taxi and run up fuel Maximum weight approved for the start of the takeoff run Maximum weight approved for the landing touchdown Maximum weight exclusive of usable fuel ISSUED JUNE 18 1976 PIPER AIRCRAFT CORP ATION 5 SECTION 1 PA 28 181 CHEROKEE HER II GENERAL lOO THIS PAGE INTENTIONALLY LEFT BLANK ISSUED JUNE 18 1976 REPORT 790 1 9 SECTION 1 PIPER AJ RAFT CORPORATION GENERAL 28 181 dEROKEE ARCHER II nn THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 1 10 PIPER AIRCRAFT gt PA 28 181 CHEROKEE ARCHER SECTION 1 GENERAL 1 21 CONVERSION FACTORS MULTIPLY acres atmospheres atm b
151. gned to operate the air driven gyro instruments This includes the directional and attitude gyros when installed The system consists of an engine driven vacuum pump a vacuum regulator a filter and 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 will become inoperative The vacuum gauge mounted on the right instrument panel to the right of the radios provides valuable information to the pilot about the operation of the vacuum system A decrease in pressure in a system that remained constant over an extended period may indicate a dirty filter dirty screens possibly a sticking aum regulator or leak in system a low vacuum indicator light is provided in the annunciator panel Zero pressure would indicate a sheared pump drive defective pump possibly a defective gauge or collapsed line In the event of any gauge variation from the norm the pilot should have a mechanic check the system to prevent possible darnage to the system components or eventual failure of the system vacuum regulator is provided in the system to protect the gyros The valve is set 50 the normal vacuum reads 5 0 x 1 inches of mercury a setting which provides sufficient vacuum to operate all the gyros at their rated RPM Higher settings will damage the gyros and with a low setting the gyros will be unreliable The regula
152. he container and expelling air from the strut chamber To allow fluid to enter the bottom chamber of the main gear strut housing the torque link assembly must be disconnected to let the strut be extended a minimum of 10 inches the nose gear torque links need not be disconnected Do not allow the strut to extend more than 12 inches When air bubbles cease to flow through the hose compress the strut fully and again check fluid level Reinstall the valve core and filler plug and the main gear torque links if disconnected With fluid in the strut housing at the correct level attach a strut pump to the air valve and with the airplane on the ground inflate the oleo strut to the correct height In jacking the aircraft for landing gear or other service two hydraulic jacks and a tail stand should be used At least 250 pounds of ballast should be placed on the base of the tail stand before the airplane is jacked up The hydraulic jacks should be placed under the jack points on the bottom of the wing and the airplane jacked up until the tail skid is at the right height to attach the tail stand After the tail stand is attached and the ballast added jacking may be continued until the airplane is at the height desired The steering arms from the rudder pedals to the nose wheel are adjusted at the nose wheel by tuming the threaded rod end bearings in or out Adjustment is normally accomplished at the forward end of the rods and should be done in such a way
153. he seat belt and adjusted to allow proper accessibility to all controls including fuel selector flaps trim etc while maintaining adequate restraint for the occupant If the inertia reel type shoulder hamess is installed a pull test of its locking restraint feature should be performed Exercise and set the flaps and trim tab Insure proper flight control movement and response All doors should be properly secured and latched On air conditioned models the air conditioner must be OFF to insure normal takeoff performance 4 23 TAKEOFF The normal takeoff technique is conventional for the Cherokee Archer The tab should be set lightly aft of neutral with the exact setting determined by the loading of the airplane Allow the airplane accelerate to 48 to 53 KIAS depending on the weight of the aircraft and ease back on the control wheel o rotate to climb attitude The procedure used for a short field takeoff with an obstacle clearance or a soft field takeoff differs lightly from the normal technique The flaps should be lowered to 25 second notch Allow the aircraft accelerate to 41 to 49 KIAS depending on the aircraft weight and rotate the aircraft to climb attitude After breaking ground accelerate to 45 to 54 KIAS depending on aircraft weight Continue to climb wh ccelerating to the flaps up rate of climb speed 76 KIAS if no obstacle is present or 64 KIAS if obstacic learance is a consideration Slowly retract the flap
154. he strap The reel will lock in place under this test and prevent the strap from extending Under normal movement the strap will extend and retract as required ISSUED JUNE 18 1976 REPORT VB 790 REVISED JULY 3 1978 7 21 PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION AND OPERATION PA 28 181 CHEROKEE ARCHER II __ 7 27 24 cubic foot baggage area located behind the rear seats is accessible either from the cabin or through an outside baggage door on the right side of the aircraft Maximum capacity is 200 pounds Tie down straps are provided and should be used at all times NOTE It is the pilot s responsibility to be sure when the baggage is loaded that the aircraft C G falls within the allowable C G Range refer to Section 6 Weight and Balance 7 29 STALL WARNING An approaching stall is indicated by a stall warning horn which is activated between five and ten knots above stall speed Mild airframe buffeting and gentle pitching may also precede the stall Stall speeds are shown on graphs in the Performance Section The stall warning horn emits a continuous sound and is activated by a lift detector installed on the leading edge of the left wing During preflight the stall warning system should be checked by turning the master switch lifting the detector and checking to determine if the horn is actuated 7 31 FINISH exterior surfaces are primed with e
155. head of the wing leading edge at the intersection 310 of the straight and tapered section 109 7 LEVELING DIAGRAM Figure 6 3 REPORT YB 790 ISSUED JUNE 18 1976 6 4 REVISED FEBRUARY 25 1977 PIPER AIRCRAFT CORPO SECTION 6 PA 28 181 CHEROKEE ARER WEIGHT AND BALANCE 2 The basic empty weight center of gravity as weighed including optional equipment full oil and unusable fuel can be determined by the following formula Arm R 1 B inches Where ISSUED JUNE 18 1976 REPORT VB 790 REVISED JANUARY 20 1977 6 5 SECTION 6 PIPERA RAFT CORPORATION WEIGHT AND BALANCE 28 181 ARCHER ___ 5 5 WEIGHT AND BALANCE DATA AND RECORD er of Gravity Location and Useful Load listed in Figure 6 5 are for the The Basic Empty Weight Cent These figures apply only to the specific airplane serial number and as licensed at the factory egistration number shown The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance Record Figure 6 7 This form is provided to present the current status of the airplane basic weight and a complete history of previous modifications Any change to the permanently installed equipment yr modification which affects weight or moment must be entered in the Weight and Balance Record REPORT VB 790 ISSUED JUNE 18 1976 6 6
156. heel and pulling it snug The flaps are locked when in the UP position and should be left retracted Tie downs can be secured to rings provided under each wing and to the tail skid The rudder is held in position by its connections to the nose wheel steering and normally does not have to be secured 4 35 STALLS The stall characteristics of the Cherokee Archer 11 are conventional approaching stall 5 indicated by a stall warning horn which is activated between five and ten miles per hour above stall speed Mild airframe buffeting and gentle pitching may also precede the stall The gross weight Stalling speed of the Cherokee Archer Il with power off and full flaps is 49 5 With the flaps up this speed is increased 6 KTS Loss 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 preflight the stall warning system should be checked by turning the master switch ON the detector and checking to determine if the horn is actuated The master switch should be returned to the OFF position after the check is complete ISSUED JUNE 18 1976 REPORT VB 790 REVISED MARCH 30 1984 4 15 SECTION 4 PIPER A RAFT CORPORATION NORMAL PROCEDURES PA 28 181 CHEROKEE ARCHER 4 37 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft it is recommended that when turbulent
157. hem 3 Allow the solvent to remain on the gear from five to ten minutes Then rinse the gear with additional solvent and allow to dry 4 Remove the cover from the wheel and remove the catch pan 5 Lubricate the gear in accordance with the Lubrication Chart c Cleaning Exterior Surfaces The airplane should be washed with a mild soap and water Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal Cover areas where cleaning solution could cause damage To wash the airplane use the following procedure 1 Flush away loose dirt with water 2 Apply cleaning solution with a soft cloth a sponge or a soft bristle brush 3 To remove exhaust stains allow the solution to remain on the surface longer 4 To remove stubborn oil and grease use a cloth dampened with naphtha 5 Rinse all surfaces thoroughly 6 Any good automotive wax may be used to preserve painted surfaces Soft cleaning cloths or a chamois should be used to prevent scratches when cleaning or polishing heavier coating of wax on the leading surfaces will reduce the abrasion problems in these areas d Cleaning Windshield and Windows 1 Remove dirt mud and other loose particles from exterior surfaces with clean water 2 Wash with mild soap and warm water or with aircraft plastic cleaner Use a soft cloth or sponge in a straight back and forth motion Do not rub harshly
158. his will cause the bearing pointer to move directly to the parked 90 position Make sure the unit is tuned to a useable frequency Now select ADF mode and the needle should move without hesitation to the station bearing Excessive sluggishness wavering or reversals indicate a signal that is too weak or a system malfunction OPERATING THE TIMERS The flight timer will always be autornatically reset to 00 whenever power is interrupted either by the avionics master switch or the unit s ON OFF switch Flight time or elapsed time are displayed and annunciated alternatively by depressing the FLT ET button The flight timer continues to count up until the unit is turned off The elapsed timer may be reset back to 00 by pressing the SET RST button It will then start counting up again NOTE Pressing the SET RST button will reset the elapsed timer whether it is being displayed or not The elapsed timer also has a count down mode To enter the countdown mode the SET RST button is depressed for about two seconds or until the ET annunciation begins to flash It is now in the ET set mode and a time up to 59 minutes 59 AFM M26 Rev 29 Nov 2005 Page 10 lt Diamond MAINTENANCE Doc No AFM M26 KR87 seconds may be preset into the elapsed timer with the concentric knobs The preset time will be displayed and remain unchanged until SET RST is pressed again which will start the elapsed timer counting down from the preset time
159. hones during cockpit communications After the operator has stopped talking the intercom channel remains momentarily open to avoid closure between words or during normal pauses The GMA 340 provides three intercom modes PILOT CREW and ALL The mode selection is accomplished using the PILOT 10 and CREW 9 buttons Pressing a button activates the corresponding ICS mode Pressing again deactivates the mode The operator can switch directly from PILOT to CREW or from CREW to PILOT by pressing the other mode button ALL mode is active when neither PILOT or CREW mode is selected These modes allow different degrees of interaction between the crew and passengers PILOT mode isolates the pilot from everyone else and dedicates the airplane radios to the pilot exclusively The copilot and passengers share communication between themselves but cannot communicate with the pilot or hear the airplane radios CREW mode places the pilot and copilot on a common ICS communication channel ALL mode allows full intercom communication between everyone plugged into the GMA 340 Airplane radios are heard by all The following table summarizes the different modes supported by the GMA 340 AFM M10 Rev 06 Feb 2006 4 Diamond Doc No AFM M10 GMA 340 PILOT HEARS COPILOT HEARS PILOT LED LIT Selected Radios Pilot Copilot CREW LED Selected Radios Pilot Selected Radios Copilot LIT Copilot
160. iate Avco Lycoming Operator s Manual when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the appropriate Speed Power graph Figure 5 19 or 5 21 Calculate the cruise fuel flow the cruise power setting from the information provided by the Lycoming Operator s Manual The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel flow by the cruise time The cruise calculations established for the cruise segment of our flight planning example are as follows 1 Total Distance 314 nautical miles 2 Cruise Distance 1 minus c 4 minus d 2 314 minus 11 5 minus 20 6 282 nautical miles 3 Cruise Power 65 rated power 4 Cruise Speed 110 KTS TAS 5 Cruise Fuel Consumption 7 6 GPH 6 Cruise Time e 2 divided by e 4 282 nautical miles divided by 110 KTS 2 56 hrs 7 Cruise Fuel 5 multiplied by 6 7 6 multiplied by 2 56 hrs 19 5 gal reference Figure 5 29 reference Figure 5 21 ISSUED JUNE 18 1976 REPORT VB 790 REVISED MAY 23 1980 5 5 SECTION 5 PIPER RAFT CORPORATION PERFORMANCE 28 181 lt ARCHER f Total Flight Time The total flight time is determined by adding the time to climb the time to descend and the cruise time Remember
161. igibility bracket for application of this handbook is 28 7790001 through 28 7990589 The specific application of this handbook is limited to the Piper PA 28 18 model airplane designated by serial number and registration number on the face of the title this handb bk pont This handbook cannot be used for operational purposes unless current i um er RR NEQUEO A m REVISIONS The information compiled in the Pilot s Operating Handbook wil be kept Current by revisions distributed to the airplane owners KE Revision material will consist of information necessary to update the text of the present handbook and or to add information to cover added airplane equipment 4 Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below 1 Revision pages will replace only pages with the same page number 2 Insert all additional pages in proper numerical order within each section 3 Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the opposite revised added or deleted material A line along the outside margin o
162. iloUflight director can bc accomplished by engaging the autopilot flight director in the ot APR mode When the autopilov flight director system is using course information supplied by GNS 430 System and the course pointer is not automatically driven to the desired track the course pointer on the HSI must be manually set to the desired track DTK indicated by the GNS 430 For detailed autopilo Night director operational instructions refer to the Approved Flight Manual Supplement for the autopilot Night director 4 AUTOMATIC LOCALIZER COURSE CAPTURE MEAS CAURE By default the GNS 430 automatic localizer course capture feature is enabled This feature provides a method for system navigation data present on the extemal indicators to be switched automatically from GPS guidance to localizer glide slope guidance at the point of course intercept on a localizer at 4 which GPS derived course deviation equals localizer derived course deviation offset from the final approach course Is being flown it is possible that the automatic switch from GPS course guidance to localizer glide slope courso guidance will not occur It is the pilot s responsibility to ensure correct system navigation data is present on the extemal indicator before continuing a localizer based approach beyond the final approach fix 5 DISPLAY OF LICHTNING STRIKE DATA Lightning strike data detected by the BFGoodrich WX 500 Stormscope will appea
163. ion with the complete handbook This supplement has been Approved as a permanent part of this handbook and must remain in handbook at all times when 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 case of malfunction DEPRESS and hold Disconnect switch on pilot s control wheel b Rocker switch on instrument panel OFF c Unit may be overpowered manually d In climb cruise or descent configuration a malfunction with a 3 second delay in recovery initiation may result in 45 bank and 180 altitude loss Maximum altitude loss measured at 149 KIAS in a descent e In approach configuration a malfunction with a second delay in recovery initiation Tesults in 18 bank and 10 altitude 1055 SECTION 4 NORMAL PROCEDURES a Engagement 1 Rocker Switch on instrument panel 2 Disconnect Switch on left hand side of pilot s contro wheel RELEASED b Disengagement 1 Depress Disconnect Switch on pilot s control wheel or 2 Rocker Switch on instrument panel OFF Heading Changes 1 Depress Disconnect Switch make Heading Change release Disconnect Switch 2 Move Trim Knob on instrument for Drift Correction from a constant heading 3 Move Turn Command Knob on instrument for right or left banked turns ISSUED JUN
164. ipment cont m Mark if Weight Arm In Moment Instl Pounds Aft Datum Lb In 29 Exhaust Gas Temperature Piper Dwg 99026 Cert Basis TC 2A13 7 55 4 39 1 Manifold Pressure Gauge Piper Spec PS50031 3 or 4 Cert Basis TC 2A13 0 9 60 8 55 3 Engine Hour Meter Piper Dwg 79548 0 Cert Basis TC 2A13 0 3 61 2 18 Clock Cert Basis TC 2A13 lt 4 62 4 25 7 Air Temperature Gauge Piper Dwg 99479 0 or 2 x 2 72 6 15 Cert Basis TC 2A13 PORT VB 790 ISSUED JUNE 18 1976 3 REVISED MAY 23 1980 PIPER AIRCRAFT CORPORATION SECTION WEIGHT AND BALANCI PA 28 181 CHEROKEE ARCHER II D Autopilots Optional Equipment 157 AutoFlite Cert Basis STC SA3066SW D 159 AutoControl Omni Coupler 1C388 Cert Basis STC SA3065SW D ISSUED JUNE 18 1976 Mark if Instl Weight Pounds Arm In Aft Datum 91 8 77 6 59 3 Momen Lb In 514 745 59 REPORT 790 6 39 ION 6 PIPER CORPORATION AND BALANCL PA 28 181 CHEROKEE ARCHER m Radio Equipment Optional Equipment Mark if Weight Arm In Moment Item Inst Pounds Aft Datum Lb In Collins VHF 250 or VHF 251 Comm Transceiver a Single pH 4 0 56 9 228 b Dual 8 1 56 9 461 Cert Basis TSO C37b C38b Collins VIR 350 or V R 351 Nav Receiver a Single LI
165. is document serves as the EASA Approved Supplement Flight Manual for the KR87 The information contained herein supplements or supersedes the basic Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Technical Visa by ACG Date European Aviation Safety Agency EASA approved Date Page 0 Doc No AFM M26 KR87 0 1 RECORD OF REVISIONS Reason Page s Date of Revision AFM Rev 29 2005 approval pate of Approval Inserted Diamond MAINTENANCE Doc No AFM M26 KR87 0 2 TABLE OF CONTENTS Page 1 GENERAL dee EUN RE 3 2 OPERATING LIMITATIONS citet erre feed apr xt d ee dt 3 3 EMERGENCY ieiunus een 3 4A NORMAL OPRERATING IPROCEDURES rasen dh 3 4B ABNORMAL OPERATING PROCEDURES 3 5 PERFORMANCE era 3 MASSAND BALANO s tis accent tet os Cu 4 7 DESCRIPTION OF THE AIRPLANE AND ITS 5 5 4 8 AIRPLANE HANDLING CARE AND 12 26 29 2005 Diamond MAINTENANCE Doc No AFM M26 KR87 1 GENERAL
166. ith dual mufflers heater shroud around the mufflers is provided to supply heat for the cabin and windshield defrosting The fixed pitch propeller is made from a one piece alloy forging ISSUED JUNE 18 1976 REPORT VB 790 REVISED MAY 23 1980 7 1 PIPER AIRCRAFT CORPORATION ECTION 7 SCRIPTION AND OPLAATION 28 181 CHEROKEE ARCHER MAIN WHEEL ASSEMBLY _ Figure 7 1 REPORT 790 ISSUED JUNE 18 1976 7 2 PIPER AIRCRAFT CORPORATION SECTION 7 28 181 CHEROKEE ARCHER II DESCRIPTION AND OPERATION 77 LANDING GEAR The three landing gears use Cleveland 6 00 x 6 wheels the main gear wheels Figure 7 1 being provided with brake drums and Cleveland single disc hydraulic brake assernblies All three wheels use 6 00 x 6 four ply rating Type III tires with tubes The nose gear is steerable through a 30 degree arc either side of center by use of the rudder pedals and brakes spring device incorporated in the rudder pedal torque tube assembly aids in rudder centering and provides rudder trim The nose gear steering mechanism incorporates a bungee assembly to reduce steering effort and to dampen shocks and bumps during taxiing shimmy dampener is 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 O inches for the main gear The standard brake system for this Cherokee consists of dual toe brakes attached to the rudder p
167. l flight altitude REPORT VB 790 34 OPEN DOOR If both upper and side latches are open the door will trail slightly open and airspeeds will be reduced slightly To close the door in flight Slow airplane to 87 KIAS Cabin vents close Storm window open latch If upper latch is open If side latch pull on armrest moving latch ha to latched position latch side latch then top latch If both latches are open CARBURETOR ICING Carburetor ON Mixture Adjust for Max Smoothness ENGINE ROUGHNESS Carburetor heat ON If roughness continues after one min Carburetor heat 0 ee nnn OFF adjust for max smoothness Electric fuel pump ON Fuel selector switch tanks Engine gauges check Magneto switch LU then then BOTH If operation is satisfactory on either one on that magneto at reduced power and full RICH mixture to first airport Prepare for power off landing JSSUED JUNE 18 1976 REVISED MAY 23 1980 PIPER AIRCRAFT CORPO SECTION 3 28 181 CHEROKEE EMERGENCY PROCEDURES NONO O THIS PAGE INTENTIONALLY LEFT BLANK ISSUED JUNE 18 1976 REPORT VB 790 3 5 PIPER CORPORATION SECT
168. lays for the Bendix King Digital ADF are shown and described are shown in the Figure below The Bendix King Digital ADF can be used for position plotting and homing procedures and for aural reception of amplitude modulated AM signals The flip flop frequency display allows switching between preselected STANDBY and ACTIVE frequencies by pressing the frequency transfer button Both pre selected frequencies are stored in a non volatile memory circuit no battery power required and displayed in large easy to read self dimming gas discharge numerics The active frequency is continuously displayed in the left window while the right window will display either the standby frequency or the selected readout from the built in electronic timer The built in electronic timer has two separate and independent timing functions An automatic flight timer that starts whenever the unit is turned on This timer AFM M26 Rev 29 Nov 2005 Diamond MAINTENANCE Doc No AFM M26 KR87 functions up to 59 hours and 59 minutes An elapsed timer which will count up or down for up to 59 minutes and 59 seconds When a preset time interval has been programmed and the countdown reaches 00 the display will flash for 15 seconds Since both the flight timer and elapsed timer operate independently it is possible to monitor either one without disrupting the other The pushbutton controls and the bearing indicators are internally lighted In
169. lever on the right side of the control quadrant may be adjusted to increase c decrease the friction holding the throttle and mixture controls or to lock the controls in a selected positio 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 REPORT VB 790 ISSUED JUNE 18 1976 7 6 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 181 CHEROKEE ARCHER II DESCRIPTION AND OPERATION CONTROL QUADRANT AND CONSOLE Figure 7 5 ISSUED JUNE 18 1976 REPORT VB 790 7 7 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA 28 181 CHEROKEE ARCHER II FUEL SELECTOR Figure 7 7 7 13 FUEL SYSTEM Fuel is stored in two twenty five gallon 24 gallons usable tanks which are secured to the leading edge structure of each wing by screws and nut plates The fuel selector control Figure 7 7 is located on the left side panel forward of the pilot s seat The button on the selector cover must be depressed and held while the handle is moved to the OFF position The button releases automatically when the handle is moved back into the ON position An auxiliary electric fuel pump is provided in case of failure of the engine driven pump The electric pump should be on for all takeoffs and landings and when switching tanks The pump switch is located in the switch panel above the throttle quadrant The fuel drains should
170. mer TRANSCEIVERS NOTE Audio level is controlled by the selected COM radio volume control Selection of either COM 1 or COM 2 13 for both MIC and audio source is accomplished by pressing either COM 1 MIC or COM 2 MIC 14 The active com audio is always heard on the headphones Each audio source can be selected independently by pressing COM 1 or COM 2 13 When selected in this way they remain active as audio sources independently of which transceiver has been selected as the active microphone source When a microphone is keyed the active transceiver s MIC button LED blinks approximately once per second to indicate the transmitter is active When no airplane radio activity is detected by the GMA 340 the amount of ambient AFM M10 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M10 340 background noise from the radios is further reduced by MASQ circuit This processing is also applied to the Nav radios SPILT COM Pressing the COM 1 2 button 15 activates the split com function While this mode is active COM 2 is dedicated solely to the copilot as a MIC audio source while COM 1 is dedicated to the pilot as a MIC audio source The pilot can still listen to NAV 1 2 DME ADF and The pilot and copilot can simultaneously transmit in this mode the pilot transmitting over COM 1 and the copilot transmitting over COM 2 The SPLIT COM mode is canceled by pressing the COM 1
171. mergency Procedures Falls aus unbekannten Gr nden der Kraftstoffvorrat im rechten Tank weiniger als sein sollte kann ausnahmsweise die Landung mit dem linken Tank ausgef hrt werden Vom Luftfahrt Bundesamt genehmigt Datum Juni 02 24 10 2001 Seite 2von2 Ausgabe 1 2 160 Suppl Chpt8 4 Diamond Mass and Balance AFM Suppl List MAINTENANCE Reg OE DKT PA 28 181 SIN 28 7890244 Man PIPER Date 22 02 06 Rev 10 340 06 02 06 12 M12 enoa 06 02 06 aa AFM M26 KR87 Diamond MAINTENANCE Doc No AFM M10 GMA 340 EASA APPROVED FLIGHT MANUAL SUPPLEMENT GMA 340 This document must be carried in the aircraft at all times It describes the operating procedures for the GMA 340 when it has been installed in accordance with the GMA 340 installation manual and EODM 101 For aircraft with EASA Approved Airplane Flight Manual this document serves as the EASA Approved Flight Manual Supplement for the GMA 340 For aircraft that do not have an approved flight manual this document serves as the EASA Approved Supplement Flight Manual for the GMA 340 The information contained herein supplements or supersedes the basic Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Tech
172. mity to ground during takeoff and landing The words master switch used hereafter in this manual indicate both sides of the switch battery si and alternator side ALT are to be depressed simultaneously to OFF or ON as directed REPORT VB 790 ISSUED JUNE 18 1976 7 10 REVISED MAY 23 1980 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 181 CHEROKEE ARCHER II DESCRIPTIUN AND OPERATION Unlike previous generator systems the ammeter does not 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 current demanded by the battery As each item of electrical equipment is turned on the current will increase to a total appearing on the ammeter This total includes the battery The average continuous load for night flight with radios on is about 30 amperes This 30 ampere value plus approximately two amperes for a fully charged battery will appear continuously under these flight conditions The amount of current shown on the ammeter will tell immediately if the alternator system is operating normally as the amount of current shown should equal the total amperage drawn by the equipment which is operating If no output is indicated on the ammeter during flight reduce the electrical load by turning off all unnecessary electrical equipment Check both 5 ampere field breaker and 60 am
173. n with suto 925 et and is critical when outside ambient temperatures are 859F or higher h and 2 contre Switches on he pilol s instrument Dangle of ihe pumps ON for takeoff landing around taxis ie el pump moy Deng jer wise Operelions prora EUR ues are maintained basic Bir plane ADDS DOE 7 3 for pump operat 4 Diamond MAINTENANCE Doc No AFM M10 GMA 340 0 3 TABLE OF CONTENTS Page 1 4 2 OPERATING LIMITATIONS nnne nnne nennen ener 4 3 EMERGENCY PROCEDURES 4 4A NORMAL OPERATING PROCEDURES senem 4 4B ABNORMAL OPERATING 8 4 5 PERFORMANCE 4 6 MASS AND eene nnne 5 if DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 5 8 AIRPLANE HANDLING CARE AND MAINTENANCE nennen 12 AFM M10 06 Feb 2006 4 Diamond MAINTENANCE Doc No AFM M10 GMA 340 1 GENERAL This Supplement supplies the information necessary for the efficient operation of
174. n For limitations procedures ead performance information not contained in this supplement consult the basic Airplsne Flight Manual Serial Number LIMITATIONS Fuel The use of leaded and unleaded automotive gasoline 91 minimum antiknock Index RON MON 2 per ASTM Specification D 439 15 approved Intermixing with aviation gasolina is also approved a fin insirument panel in fuil vizw of the pilot AND LANDING ON RIGHT TANK WHEN OPERATING WITH AUTO GAS See Procedures Section of his Supplement Near existing AY GAS placards al each fuel servicing FUEL UNLEADED GR LEADED AUTOMOTIVE BASOLIHE 91 HALE AUT 165 FON 72 PER 4911 0 419 WITH AVIATION GASOLINE ALSO APPROVED DO USE FLIEL THAT CONTAINS USE ONLY PETROLEUM BASED GASOLINE PROCEDURES SECTION Emergency Procedures 1 for reeson fuel quantity on the right lank is near ly cepleted less than 1 4 full landing may be eccomplished on the tank Normal Procedures Fuel Selector 5 1 Use Right tank for takeoff and landing when operating gas including when it is inter mixed with aviation gesoline Fuel Management 1 Fuel lank usage shall be plenned such that sufficient fuel no less then 1 4 full remains nl the right hand tank for all nor mal operations This applies whe
175. n riugzeugs beigef gt sein wenn das Flugzeug durch EMZ Nr SA 1231 modifiziert wurde Die in diesem Anhang enthaltenen Informationen erganzen oder ersetzen diejenigen des Originelhandbuches nur in den folgenden Bereichen F r Beschr nkungen Verfahren und Leistungsangaben die in diesem Anhang nicht enthalten sind ist das Originalhandbuch zu konsultieren Beschr nkungen Limitations Zus tzlich zu den im Original Flughandbuch aufgef hrten Kra amp stoffen sind Kraftstoff folgende Kraftstoffe zugelassen Unverbleiter Automobilkraftstoff nach DIN EN 228 ROZ 98 Unverbleiter Automobilkraftstoff gem ASTM Spezifikation D 439 mit einem Antiknockindex von mindestens 91 Oktan ROZ MOZ 2 Verbleiter Automobilkraftstoff gem ASTM Spezifikation D 439 mit einem Antiknockindex von mindestens 91 Oktan ROZ MOZ 2 Das Mischen mit AVGAS Flugzeugkraftstoff ist gestattet Es d rfen nur Kraftstoffe mit einem Alkoholgehalt von maximal 196 verwendet werden Falls diese Information nicht vorliegt bzw dieser Kraftstoff nicht verf gbar ist muss AVGAS getankt werden entsprechend den Angaben des Flughandbuches Kraftstoff nach DIN EN 228 kann Bis zu 5 Alkohol enthalten Anmerkung Beschriftung Neben den bestehenden AVGAS Beschriftungen ist an jeder Tankeinf ll ffnung ein Aufkleber mit dem folgenden Text anzubringen Seile 1 von 2 Ausgabe 1 28 169 gt 4 Herme n Blenkstr 28 3810 unschweig Instr
176. nbound course heading to the airport Select LOC REV mode with coupler and HDG mode on the autopilot console SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook necessary for this supplement REPORT VB 790 ISSUED JUNE 18 1976 9 10 PIPER AIRCRAFT CORPORATION SECTION 9 28 181 CHEROKEE ARCHER II SUPPLEMENTS LT MT THIS PAGE INTENTIONALLY LEFT BLANK ISSUED JUNE 18 1976 REPORT 790 9 11 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 181 CHEROKEE ARCHER a THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 9 12 PIPER AIRCRAFT CORPORATION SECTION 9 SUPPLEMENTS PA 28 181 CHEROKEE ARCHER II ____ SUPPLEMENT 4 PIPER ELECTRIC PITCH TRIM SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Piper Electric Pitch Trim is installed The information contained within this supplement is to be used as described in conjunction with the complete handbook This supplement has been FAA Approved asa permanent part of this handbook and must remain in us handbook at all times 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 supplement n SECTION 3 EMERGENCY PROCEDURES
177. nce rd for this information ity Category Operation No baggage or rear passengers allowed WEIGHT AND BALANCE LOADING FORM Figure 6 11 VB 790 ISSUED JUNE 18 1976 CTION 6 PIPER AIRCRAFT CORPORATION SE WEIGHT AND BALANCE 28 181 CHEROKEE ARCHER II LOAD WEIGHT POUNDS Shear sar ot OT Lar LLLLLLLLLLTAIA 0 5 10 15 20 25 30 40 50 MOMENT 1000 POUNDS INCHES LOADING GRAPH Figure 6 13 REPORT VB 790 ISSUED JUNE 18 1976 6 13 CTION 6 AND BALANCE PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER II WEIGHT IN POUNDS JRT VB 790 84 86 88 90 INCHES AFT OF DATUM C G RANGE AND WEIGHT Figure 6 15 ISSUED JUNE 18 1976 REVISED MAY 23 1980 PIPER AIRCRAFT CORPORATION SECTION 6 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE THIS INTENTIONALLY LEFT BLANK ISSUED JUNE 18 1976 REPORT VB 790 6 15 PIPER AIRCRAFT CORPORATION TION 6 IGHT AND BALANCE 28 181 CHEROKEE ARCHER II Nee eT nn nn THIS PAGE INTENTIONALLY LEFT BLANK PORT VB 790 ISSUED JUNE 18 1976 6 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE 6 9 EQUIPMENT LIST The following is a list of equipment which may be installed in the PA 28 181 t consists of those items used for defining the configuration of an airpla
178. nd 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 unless otherwise placarded Both the pitot and static lines can be drained through separate drain valves located on the left lowe side of the fuselage interior heated pitot head which alleviates problems with icing and heavy rain is available as optional equipment The switch for the heated pitot head is located on the electrical switch panel to the left of the right control wheel To prevent bugs and water from entering the pitot and static pressure holes a cover should be placed over the pitot head A partially or completely blocked pitot head will give erratic or zero readings on the instruments NOTE During the preflight check to make sure the pitot cover is removed REPORT VB 790 ISSUED JUNE 18 1976 7 18 REVISED JULY 12 1977 lt PIPER AIRCRAFT CORPORATION Bes SECTION 7 PA 28 181 CHEROKEE ARCHER DESCRIPTION AND OPERATION ALTIMETER AIRSPEED INDICATOR PITOT HEAT SWITCH VERTICAL SPEED INDICATOR PITOT HEAD DRAIN VALVES ALTERNATE STATIC SOURCE 1 2 3 4 5 6 7 PITOT STATIC SYSTEM Figure 7 17 ISSUED JUNE 18 1976 REPORT VB 79 7 19 PA 28 181 CHEROKEE ARCHER PIPER AIRCRAFT CORPORATION DESCRIPTION AND ATION SECTION 7 HEATING AND VENTILATING SYSTEM HI
179. ne when the basic empty weight is established at the time licensing Only those standard items which are alternate standard items and those required to be listed by the certificating authority are presented Items marked with an X are those items which were installed on the airplane described below as delivered by the manufacturer PIPER AIRCRAFT CORPORATION 28 181 CHEROKEE ARCHER 5 PET RIAL No _ 26 0 29 _ 4 8 722 Propeller and Propeller Accessories Item if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In 1 Propeller Sensenich 76EM8S5 0 60 Piper Spec 550077 8 Cert Basis TC 3 Propeller Sensenich 76 855 0 62 Piper 550077 42 Cert Basis TC P4EA ISSUED JUNE 18 1976 REPORT REVISED MARCH 30 1984 6 PIPER AIRCRAFT CORPORATION SHT AND BALANCE PA 28 181 CHEROKEE ARCHER nn THIS PAGE INTENTIONALLY LEFT BLANK PORT VB 790 ISSUED JUNE 18 1976 8 PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER II b Engine and Engine Accessories Item No Item 11 Engine n a Piper Dwg 62941 16 Lycoming Model O 360 A4M Cert Basis TC E286 b Piper Dwg 62941 17 Lycoming Model O 360 A4A Cert Basis TC 286 13 Oil Filter Lycoming No 75528 AC OF5578770 Cert Basis TC E286 15 Filter Lycoming LW 13743 Champion 48
180. ng System is installed in accordance with STCH SA00705W The information contained herein supplements the information of the basic Airplane Flight Manual For Limitations Procedures and Performance information not contained in this Supplement consult the basic Airplane Flight Manual FAA APPROVED 4 2 Rathgeber Manager Aircraft Certification Office Federal Aviation Administration Wichita Kansas 67209 Date 11 21 02 GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER LOG OF REVISIONS Revision Page FAA Date of Number Number s Approved Approval All Initial Release Baker 10 02 98 Add BFGoodrich WX Baker 500 and SKY WATCH Interfaces Remove SKYWATCH 11 21 02 and add GTX 330 TIS LE For Manager Wichita Aircraft Certification Office PIPER PA32 190 00140 03 Rev C FAA APPROVED Pape 2 of 10 DATE 11 21 02 GARMIN Intemational Inc 1200 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER Table of Contents SECTION PAGE GENERAL acce tincdunt te e M scd NS 4 LIMITATIONS und EMERGENCY PROCEDURES NORMAL PROCEDURES 8 PIPER 2 FAA APPROVED 190 00140 03 Rev C DATE
181. nical Visa by Date European Aviation Safety Agency EASA approved Date 0 Diamond MAINTENANCE Doc No AFM M10 GMA 340 0 1 RECORD OF REVISIONS Rev Reasc Reason A Page s Date of of approval pate o Date Signature No ter Revision Approval Inserted Diamond MAINTENANCE Doc No AFM M10 GMA 340 0 2 LIST OF EFFECTIVE PAGES 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 1 2 3 4A 4B 5 06 Feb 2006 6 7 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 AFM M10 06 Feb 2006 eter san Aviation Inc Supplement No 1 1 5 18 inden Nebreske 68959 22 gt APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR Piper 28 160 23 6710 23 1760 28 1761 10 28 4377 28 161 26 7716001 1028 8116001 amp 28 180 28 671 028 1760 28 1761 10 28 5859 28 7105001 to 28 7505261 pa 28 181 A 7 28 7690001 to 28 7990626 OE DKT Registration Number 11 28 7990244 This Supplement must be attached to the FAA Approved Airplane Flight Manual spplicable to that particular airplane when the airplane hes been modified In accordance with STC SA2660CE The Information contain d herein supplements or Supersedes the besic manual only In those areas listed herei
182. o make sure they open Next complete a check of the landing gear Check the main gear shock struts for proper inflation There should be 4 50 inches of strut exposure under a normal static load The nose gear should bc checked for 3 25 inches of strut exposure Check all tires for cuts and wear and insure proper inflation Make a visual check of the brake blocks for wear or damage Remove the cover from the pitot head on the underside of the left wing Check the pitot head to make sure the holes are open and clear of obstructions Don t forget to clean and check the windshield The propeller and spinner should be checked for defects or nicks Lift the cowling and check for any obvious fuel or oil leaks Check the oil level Make sure that the dipstick has properly seated after checking Secure the cowling and check the inspection covers Check the air inlets for foreign matter and the alternator belt for proper tension Stow the tow bar and check the baggage for proper storage and security The baggage compartment doors should be closed and secure Upon entering the aircraft ascertain that all primary flight controls operate properly Close and secure the cabin door and check that all the required papers are in order and in the airplane Fasten and adjust the seat belts and shoulder harness and check the function of the inertia reel by pulling sharply on the strap Fasten seat belts on empty seats NOTE If the fixed shoulder h
183. of the baggage compartment The regulator and overvoltage relay are located on the forward left side of the fuselage behind the instrument panel Electrical switches are located on the right center instrument panel and the circuit breakers are located on the lower right instrument panel rheostat switch on the left side of the switch panel controls the navigational lights and the radio lights The similar switch on the right side controls and dims the panel lights Standard electrical accessories include a starter electric fuel pump stall warning indicator cigar lighter fuel gauge ammeter and annunciator panel The annunciator panel includes alternator and low oil pressure indicator lights When the optional gyro system is installed the annunciator panel also includes a low vacuum indicator light The annunciator panel lights are provided only as a warning to the pilot that a system may not be operating properly and that he should check and monitor the applicable system gauge to determine when or if any necessary action is required Optional electrical accessories include navigation lights anti collision light landing light instrument lighting and cabin dome light Circuits will handle the addition of communications and navigational equipment WARNING Strobe lights should not be operating when flying through overcast and clouds since reflected light can produce spacial disorientation Do not operate strobe lights in close proxi
184. oler duct on the right rear engine baffle This plate should be installed whenever the ambient temperature reaches 50 F or less The plate should be removed and stored in the cockpit when the ambient temperature exceeds 50 F It is recommended that an optional Engine Breather Tube Winterization Kit be installed for cold weather operation This kit is available through your Piper Dealer Distributor ISSUED JUNE 18 1976 eus REVISED JULY 3 1978 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICIN ND MAINTENANCE PA 28 181 CHEROKEE ARCHER II a THIS PAGE INTENTIONALLY LEFT BLANK REPORT 790 ISSUED JUNE 18 1976 8 16 SECTION 9 SUPPLEMENTS SECTION 9 SUPPLEMENTS E TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph Supplement Page No No General doeet E LE eunt eua 9 1 1 Air Conditioning System 1 9 3 2 II Autopilot Installation 9 7 AutoControl Autopilot Installation 9 9 4 Piper Electric Pitch Tim Sai acd sap tre Bos ORTUS V 9 13 REPORT VB 790 94 PIPER AIRCRAFT CORPORATION SECTION 9 SUPPLEMENTS 28 181 CHEROKEE ARCH R II SECTION 9 SUPPLEMENTS 9 1 GENERAL 3 the form of Supplements which are necessary for ef
185. ompartment place a strip of tape on the magneto vents to prevent any solvent from entering these units 1 Place alarge pan under the engine to catch waste 2 With the engine cowling removed spray or brush the engine with solvent or a mixture of solvent and degreaser In order to remove especially heavy dirt and grease deposits it may be necessary to brush areas that were sprayed CAUTION Do not spray solvent into the alternator vacuum pump starter or air intakes 3 Allow the solvent to remain on the engine from five to ten minutes Then rinse the engine clean with additional solvent and allow it to dry REPORT VB 790 ISSUED JUNE 18 1976 8 13 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICIN MAINTENANCE 28 181 CHEROKEE ARCHER II __ CAUTION Do not operate the engine until excess solvent has evaporated or otherwise been removed 4 Remove the protective tape from the magnetos 5 Lubricate the controls bearing surfaces in accordance with the Lubrication Chart b Cleaning Landing Gear Before cleaning the landing gear place plastic cover or similar material over the wheel and brake assembly 1 Place a pan under the gear to catch waste 2 Spray or brush the gear area with solvent or a mixture of solvent and degreaser as desired Where heavy grease and dirt deposits have collected it may be necessary to brush areas that were sprayed in order to clean t
186. or remaining within the operating limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to increase its in flight capabilities it should not be used solely as an occasional operating reference The pilot should study the entire handbook to familiarize himself with the limitations performance procedures and operational handling characteristics of the airplane before flight The handbook has been divided into numbered arabic sections each provided with a finger tip tab divider for quick reference The limitations and emergency procedures have been placed ahead of normal procedures performance and other sections to provide easier access to information that may be required in flight The Emergency Procedures Section has been furnished with red tab divider to present an instant reference to the section Provisions for expansion of the handbook have been made by the deliberate omission of certain paragraph numbers figure numbers item numbers and pages noted as being left blank intentionally ISSUED JUNE 18 1976 REPORT VB 790 1 1 SECTION 1 PIPER RAFT CORPORATION GENERAL 28 18 ARCHER Il Wing Area sq ft 170 0 Min Turning Radius ft 30 0 from pivot point to wingtip REPORT 790 ISSUED JUNE 18 1976 1 2 PIPER AIRCRAFT ORATION 28 181 ARCHER L3 ENGINE
187. or Transmitter C C C Model CIR 11 2 a Antenna and Coax b Shelf and Access Hole Basis TSO C91 Weight includes dual antenna and cable Weight includes antenna and cable VB 790 48 Mark if Inst HE E EE I lt gt CX CA A 00 4 Omm oer Arm In Aft Datum 91 2 107 6 91 2 107 6 57 3 1957 125 7 147 5 120 0 154 0 150 0 144 3 170 7 147 5 236 2 224 4 235 4 PIPER AIRCRAFT CORPORATION PA 28 181 CHEROKEE ARCHER Moment Lb In 547 1926 547 1926 172 274 88 118 108 431 60 202 256 74 402 118 ISSUED JUNE 18 1976 REVISED APRIL 13 1979 PIPER AIRCRAFT CORPORATION SECTION 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCI ee nn nn Radio Equipment Optional Equipment cont Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In 280 Emergency Locator Transmitter Narco Model ELT 10 3 5 236 2 827 0 3 224 4 67 b Shelf and Access 0 5 235 4 118 Cert Basis TSO C91 281 Microphone a Piper Dwg 68856 10 RR 0 3 64 9 19 b Piper Dwg 68856 11 0 6 69 9 42 Piper Dwg 68856 12 0 3 64 9 19 Cert Basis 2A13 283 Boom Microphone Headset Piper Dwg 37921 2 Cert Basis TC 2A13 0 3 80 5 24 285 Cabin Speaker Cert Basis TC 2A13 0 8 99 0 79 287 Head
188. ordance with the GI 106A installation manual and EODM 101 For aircraft with EASA Approved Airplane Flight Manual this document serves as the EASA Approved Flight Manual Supplement for the CDI 1 106 For aircraft that do not have an approved flight manual this document serves as the EASA Approved Supplement Flight Manual for the CDI GI 106A The information contained herein supplements supersedes basic Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Technical Visa by ACG Date European Aviation Safety Agency EASA approved Date Page 0 4 Diamond MAINTENANCE Doc No AFM M12 GI 106A 0 1 RECORD OF REVISIONS v Reason Je Pa Page s pate of Te pate of Date Signature Revision Approval Inserted Diamond MAINTENANCE Doc No AFM M12 GI 106A 0 2 LIST OF EFFECTIVE PAGES Chapter 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 06 Feb 2006 AFM M12 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M12 GI 106A 0 3 TABLE OF CONTENTS Page 1 d EE 4 2 OPERATING 4 Pe EMERGENCY PROCEDURES auctae schonen uer 4 4 NORMAL OPERATING PROCEDURES e 4 4B ABNORMAL OPERATING PROCEDURES
189. ort period of time the engine warranty is invalidated by the use of lower octanes Refer to the latest issue of Lycoming Service Instruction No 1070 for alternate fuels and additional information ISSUED JUNE 18 1976 REPORT VB 790 REVISED JUNE 8 1990 8 11 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERVICING AND MAINTENANCE PA 28 181 CHEROKEE ARCHER II M summary of the current grades as well as the previous fuel designations is shown in the following chart FUEL GRADE COMPARISON CHART Current Commercial Fuel Grades ASTM D910 75 Current Military Fuel Grades MIL G 5572F Previous Commercial Fuel Grades ASTM D910 Max TEL Max TEL Max TEL Grade Color ml U S gal Color ml U S gal Color mI U S gal 80 87 red 0 5 80 87 red 0 5 91 96 blue 2 0 none none none 100 130 green 3 0 100 130 blue 2 0 115 145 purple 4 6 115 145 purple 4 6 Grade 100LL fuel in some overseas countries is currently colored green and designated as 100L 7 Commercial fuel grade 100 and grade 100 130 having TEL content of up 4 ml U S gallon are approved for use in all engines certificated for use with grade 100 130 fuel The operation of the aircraft is approved with an anti icing additive in the fuel When an icing additive is used it must reflect the specification MIL I 27686 must be uniformally blended with the fuel whil
190. ot ICS Voice Activated VOX Intercom Level Copilot and Passenger ICS Volume Control Pull out for Passenger Volume Co Or Copilot and Passenger VOX Intercom Squelch Level Ko Crew Isolation Intercom Mode Button EN Pilot Isolation Intercom Mode Button Passenger Address Function Button Em Speaker Function Button Transceiver Audio Selector Buttons COM 1 COM 2 COM 3 Transmitter Audio Mic Selection Buttons AFM M10 Rev 06 Feb 2006 ab Diamond MAINTENANCE Doc No AFM M10 GMA 340 15 Split COM Button 16 Airplane Radio Audio Selection Buttons NAV 1 NAV 2 DME ADF 17 Annunciator Test Button 18 Locking Screw Access 19 Photocell Automatic Annunciator Dimming ON OFF AND FAILSAFE OPERATION FAILSAFE OPERATION The GMA 340 is powered off when the left small knob item 5 is rotated fully counter clockwise into the detent To turn the unit on rotate the knob clockwise past the click The knob then functions as the pilot s ICS volume control A failsafe circuit connects the pilot s headset and microphone directly to COM 1 in case the power is interrupted or the unit is turned off LIGHTING The intensity of the LED button annunciator and marker beacon lamps are controlled automatically by a built in photocell 19 on the front panel Nomenclature backlighting is controlled by the airplane instrument light dim
191. peed except in smooth air and then only with caution 125 12 gt Design Maneuvering Speed V4 Do not make full or abrupt control movements above this speed At 2550 LBS G W 113 111 At 1634 LBS G W 89 89 CAUTION Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced Linear interpolation may be used for intermediate gross weights Manuevering speed should not be exceeded while operating in rough air Maximum Flaps Extended Speed Vre Do not exceed this speed with the flaps extended 102 100 ISSUED JUNE 18 1976 REPORT VB 790 REVISED MARCH 30 1984 2 1 SECTION 2 IMITATIONS ns 5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line Never Exceed Yellow Arc Caution Range Smooth Air Only Green Arc Normal Operating Range White Arc Flap Down 2 7 POWER PLANT LIMITATIONS a b c 8 i G k Number of Engines Engine Manufacturer Engine Model No Engine Operating Limits 1 Maximum Horsepower 2 Maximum Rotation Speed RPM 3 Maximum Oil Temperature Oil Pressure Minimum red line Maximum red line Fuel Pressure Minimum red line Maximum red line Fuel Grade AVGAS ONLY minimum octane Number of Propellers Propeller Manufacturer Propeller Model Propeller Diameter Minimum Maximum Propeller Tolerance static RPM at maximum permissible throttle setting No addi
192. pere output breaker and reset if open If neither circuit breaker is open turn off the ALT switch for 1 second to reset the voltage relay If ammeter continues to indicate no output maintain minimum electrical load and 1ninate flight as soon as practical CAUTION Do not use cigar lighter receptacles as power sources for any devices other than the cigar lighters supplied with the airplane Any other device plugged into these receptacles may be damaged ISSUED JUNE 18 1976 REPORT 790 REVISED MARCH 30 1984 7 11 PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION AND PA 28 181 CHEROKEE ARCHER II STARTER ACCESSORIES ALTERNATOR FELD UN LINE JL ALTERNATOR 7 SOURCE POWER RELAY ENERGIZING CIRCUIT REGULATOR ALTERNATOR AND STARTER SCHEMATIC Figure 7 11 REPORT VB 790 ISSUED JUNE 18 1976 7 12 PIPER AIRCRAFT CORPORATION SECTION 7 28 181 DESCRIPTION AND OPERATION p CIRCUIT BREAKER PANEL Figure 7 13 ISSUED JUNE 18 1976 REPORT VB 790 7 13 PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION AND OPExATION PA 28 181 CHEROKEE ARCHER II THIS INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 7 14 PIPER AIRCRAFT CORPORATION SECTION 7 28 181 CHEROKEE ARCHER DESCRIPTION AND OPERATION 7 17 VACUUM SYSTEM The vacuum system is desi
193. pped with a portable antenna to allow the locator to be removed from the aircraft in case of an emergency and used as a portable signal transmitter The locator should be checked during the ground check to make certain the unit has not been accidentally activated Check by tuning a radio receiver to 121 50 MHz If there is an oscillating sound the locator may have been activated and should be turned off immediately Reset to the ARM position and check again to irre against outside interference REPORT VB 790 ISSUED JUNE 18 1976 7 25 REVISED APRIL 13 1979 PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION AND OPERATION 28 181 CHEROKEE ARCHER THIS PAGE INTENTIONALLY LEFT BLANK REPORT 790 ISSUED JUNE 18 1976 7 26 SECTION 8 AIRPLANE HANDLING SERVICE amp MAINTENANCE SECTION 8 AIRPLANE HANDLING SERVICE amp MAINTENANCE 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE Paragraph Page No No 8 1 General soa sauro cui ena pe qd ER ERU RADAR DU VR OE HE DS ae Lulu 8 1 Airplane Inspection Periods u u ne sun 8 3 Preventive Maintenance 8 4 5 7 Airplane Alterations hs 8 5 8 9 Ground Handling i ais nv mn exe te wees eh LL 8 6 8 11 Engine Filter se mir WR OW Cx WE OY vo cco
194. presence of fire is noted through smoke smell and heat in the cabin 1t is essential that the source of the fire be promptly identified through instrument readings character of the smoke or other indications since the action to be taken differs somewhat in each case Check for the source of the fire first If an electrical fire is indicated smoke in the cabin the master switch should be turned OFF The cabin vents should be opened and the cabin heat tumed OFF landing should be made as soon as possible an engine fire is present switch the fuel selector to and close the throttle The mixture shy be at idle cut off Tum the electric fuel pump OFF In all cases the heater and defroster should be OFF If radio communication is not required select master switch OFF Proceed with power off landing procedure NOTE The possibility of an engine fire in flight is extremely remote The procedure given is general and pilot judgment should be the determining factor for action in such an emergency 3 17 LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete A partial loss of pressure usually indicates a malfunction in the oil pressure regulating system and a landing should be made as soon as possible to investigate the cause and prevent engine damage A complete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty gauge In either c
195. ption from the station tuned and is usually used for identification The bearing pointer in the 227 indicator will be deactivated and immediately tum to the 90 relative position and remain there during ANT reception The ADF mode is selected and annunciated when the ADF button is in the depressed position ADF activates the bearing pointer in the KI 227 indicator causing it to move without hesitation to the point in the direction of the station relative to the airplane heading The compass card on the 227 may be rotated as desired by using the heading knob NOTE The 227 indicator has a slaved compass card The magnetic heading of the airplane will be under the lubber line The indication of this compass card should be compared with that of the KI 525A master indicator from time to time Check especially after Steep bank turns and taxi turns If a discrepancy between the two readings exists the KI 227 compass card should be synchronized to the 525A compass card by rotating the SYNC knob on AFM M26 Rev 29 Nov 2005 4 Diamond MAINTENANCE Doc No AFM M26 KR87 the indicator Some stations are unmodulated and use an interrupted carrier for identification purposes The BFO mode activated and annunciated when the BFO button is depressed permits the carrier wave and the associated Morse code identifier broadcast on the carrier wave to be heard ADF TEST PRE FLIGHT OR IN FLIGHT Select ANT mode T
196. r on the moving map and weather pages of the GNS 430 For detailed operating instructions regarding the interface of Ihe GNS 430 with the WX 500 refer to WX 500 Pilot s Guide and the GNS 430 Pilot s Guide Addendum for the WX 500 Stormscope interface PIPER PA32 FAA APPROVED 190 00140 03 Rev C DATE 11 21 02 Page 9 of 10 GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER 6 DISPLAY OF TRAFFIC INFORMATION SERVICE DATA TIS surveillance data uplinked by Air Traffic Control ATC radar through the GTX 330 Mode S Transponder will appear on the moving map and display pages of the GNS 430 For detailed operating instructions regarding the interface of the GNS 430 with the GTX 330 refer to the GNS 430 Pilot s Guide Addendum for the TIS System interface SECTION V PERFORMANCE change SECTION VI WEIGHT AND BALANCE Sec current weight and balance data SECTION AIRPLANE amp SYSTEM DESCRIPTIONS See GNS 430 Pilot s Guide for a complete description of the GNS 430 system PIPER PA32 190 00140 03 Rev A TAA APPROVED Page 10 of 10 DATE 11 21 02 PIPER AIRCRAFT CORPORATION SECTION 4 PA 28 181 CHEROKEE ARCHER II NO AL PROCEDURES TID 2 4 4 D H H
197. ration with carburetor heat as the air is unfiltered The electric fuel pump should be tumed OFF after starting or during warm up to make sure that the engine driven pump is operating Prior to takeoff the electric pump should be turned ON again to prevent loss of power during takeoff should the engine driven pump fail Check both oil temperature and oil pressure The temperature may be low for some time if the engine is being run for the first time of the day The engine is warm enough for takeoff when the throttle can be opened without the engine faltering REPORT VB 790 ISSUED JUNE 18 1976 4 11 PIPER RAFT CORPORATION SECTION 4 NORMAL PROCEDURES 28 18 dEROKEE ARCHER II e 4 21 BEFORE TAKEOFF All aspects of each particular takeoff should be considered prior to executing the takeoff procedure Turn ON the master switch and check and set all of the flight instruments as required Check the uel selector to make sure it is on the proper tank fullest Turn ON the electric fuel pump and check engine gauges The carburetor heat should be in the OFF position seat backs should be erect re should be set and the primer checked to insure that it is locked The seat belts and The mixtu s should be fastened and adjusted Fasten the seat belts snugly around the empty seats shoulder harnes NOTE If the fixed shoulder harness non inertia reel type is installed it must be connected to t
198. retor heat cherk Engine is warm for takeoff when throttle car opened without engine faltering Electric fuel pump Fuel pressure t ntn check Throttle seem m retard ISSUED JUNE 18 1976 REVISED JULY 12 1977 PIPER AIRCRAFT CORPOi PA 28 181 CHEROKEE ARCHER II BEFORE TAKEOFF Master switch ON Flight instruments check Fuelselector proper tank Electric fuel pump ON Engine gauges Check Carburetor heat ihr ge OFF Seat backs MixtuTe u Sos once asi Pel set Primer is 5 locked Belts 5 fastened adjusted Er Beats 5 seat belts sn gly fastened PIDE v Sw RSS rpm set TM Eb ex WX ru oe CORONIS set ine ex ose vus s ree free DOORS ESTO latched ALP COMMONER cud ena vv f OFF TAKEOFF NORMAL Flaps un els EN OSA D 3 set Tab xus wis sie Fa set Accelerate to 52 to 65 KIAS Control wheel back pressure to rotate to climb attitude SHORT FIELD OBSTACLE CLEARANCE ned sss 25 second notch Accelerate to 41 to 49 KIAS depending on aircraft weight Control wheel back pressure to
199. right is required to re intercept the course The procedure for flying outbound from a VOR station is the same as flying inbound except the OBS knob is first rotated to cause FROM indication to appear with the pointer centered AFM M12 Rev 06 Feb 2006 Diamond MAINTENANCE Doc No AFM M12 GI 106A To intercept a selected VOR radial from the station and fly outbound turn the OBS knob to set the desired radial under the top indicator index Maneuver the airplane to fly the selected radial magnetic heading plus or minus 45 which will provide a sufficient intercept angle The intercept angle should be reduced as the deviation needle approaches an on course condition center to prevent excessive course bracketing LOCALIZER OPERATION Select the desired localizer frequency and observe that the localizer flag is concealed The TO FROM indicator is not functional for localizer operation When flying on the front course or outbound on the back course make corrections toward the localizer vertical needle deflection The localizer path narrows as the approach end of the runway becomes closer When flying inbound on the back course or outbound on the front course the corrections are made away from the direction of needle deflection A helpful hint when flying the localizer is to set the localizer heading on the OBS dial under the lubber line for quick reference GLIDESLOPE OPERATION The glideslope horizontal d
200. rol clockwise for increased cooling counterclockwise for decreased cooling Located inboard of the temperature control is the fan speed switch and the air conditioning switch The fan can be operated independently of the air conditioning However it must be on for air conditioner operation Turning either switch off will disengage the compressor clutch and retract the condenser door Cooling air should be felt within one minute after the air conditioner is turned on NOTE If the system is not operating 5 minutes the system OFF until the fault is corrected The switch allows operation of the fan with the air conditioner turned to aid cabin air circulation if desired A LOW MED or HIGH flow of air can be selected to the air conditioner outlets located in the overhead duct The outlets can be adjusted or turned off by each occupant to regulate individual cooling effect The DOOR indicator light is located to the left of the radio stack in front of the pilot The illuminates whenever the condenser door is open and remains on until the door is closed circuit breaker located on the circuit breaker panel protects the air conditioning electrical system Whenever the throttle is in the full throttle position it actuates a micro switch which disengages the compressor and retracts the scoop This is done to obtain maximum power and maximum rate of climb The fan
201. rotate to climb attitude Afte hreaking ground accelerate to 45 to 54 dei ngon aircraft weight Acce erate 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 76 KIAS ISSUED JUNE 18 1976 REVISED MARCH 30 1984 7 SECTION 4 NORMAL PROCEDURES SOFT FIELD as 25 second notch Accelerate to 4 to 49 KIAS depending on aircraft weight Control wheel back pressure to rotate to climb attitude After breaking ground accelerate to 45 to 4 KIAS depending on aircraft weight Accelerate to best flaps up rate of climb speed 76 slowly Best rate flaps 76 KIAS Best angle flaps up 64 KIAS 2 34 lave 87 KIAS Electric fuel pump OFF at desired altitude CRUISING Reference performance charts and Avco Lycoming Operator s Manual Normal max power 75 POWER set per power table ouk adjust DESCENT Normal Ihrottle au ansehe 2500 rpm Airspeed sense nee 126 KIAS Mixture a Carburetor On if required DESCENT Power off Carburetor On if required wale tans Closed Airsp
202. rted maneuvers approved ISSUED JUNE 18 1976 REVISED MAY 23 1980 PIPER AIRCRAFT CORP SECTION 2 28 181 CHEROKEE A LIMITATIONS _________ 2 19 TYPES OF OPERATION The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135 Day V F R b Night V F R c Day LF R d Night LF R e Non Icing UEL LIMITATIONS Total Capacity 50 U S GAL 5 Unusable Fuel 2U S GAL The unusable fuel for this airplane has been determined as 1 0 gallon in each wing in critical flight attitudes c Usable Fuel 48 0 5 GAL The usable fuel in this airplane has been determined as 24 0 gallons in each wing ISSUED JUNE 18 1976 REPORT VB 790 2 5 PIPERA CORPORATION SECTION 2 LIMITATIONS 28 18 HEROKEE ARCHER ____________ THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 790 ISSUED JUNE 18 1976 26 PIPER AIRCRAFT CORPOR SECTION 2 LIMITATIONS PA 28 181 CHEROKEE ARCHER II 2 23 PLACARDS In full view of the pilot THIS AIRPLANE MUST BE UTILITY CATEGORY AIRPLANE OPERATED AS A NORMAL OR IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS ALL MARKINGS AND PLACARDS ON THIS AIRPLANE APPLY TO ITS OPERATION AS A UTILITY CATEGORY AIRPLANE FOR NORMAL AND UTILITY CATEGORY OPERATION REFER TO THE PILOT S OPERATING HANDBOOK
203. s service All other aircraft maintenance must be accomplished by a person or facility appropriately certificated by the Federal Aviation Administration FAA to perform that work Anytime maintenance is accomplished an entry must be made in the appropriate aircraft maintenance records The entry shall include 1 The date the work was accomplished 2 Description of the work 3 Number of hours on the aircraft 4 The certificate number of pilot performing the work 5 Signature of the individual doing the work REPORT VB 790 ISSUED JUNE 18 1976 8 4 REVISED JUNE 8 1990 PIPER AIRCRAFT CORPORATION SECTION 8 PA 28 181 CHEROKEE ARCHER II HANDLING SERVICINGAND MAINTENANCE 8 7 AIRPLANE ALTERATIONS lf the owner desires to have his aircraft modified he must obtain FAA approval for the alteration Major alterations accomplished in accordance with Advisory Circular 43 13 2 when performed by anA amp P mechanic may be approved by the local FAA office Major alterations to the basic airframe or systems not covered by AC 43 13 2 require a Supplemental Type Certificate The owner or pilot is required to ascertain that the following Aircraft Papers are in order and in the aircraft be displayed in aircraft at all times 1 Aircraft Airworthiness Certificate Form FAA 8100 2 2 Aircraft Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station License if transmitters are installed b To b
204. s while climbing out REPORT VB 790 ISSUED JUNE 18 1976 4 12 REVISED MARCH 30 1984 PIPER AIRCRAFT CORP SECTION 4 PA 28 181 CHEROKEE ARCHER II NORMAL PROCEDURES eS 4 25 CLIMB The best rate of climb at gross weight will be obtained at 76 KIAS The best angle of climb may be obtained at 64 KIAS At lighter than gross weight these speeds are reduced somewhat For climbing en route a speed of 87 KIAS is recommended This will produce better forward speed and increased visibility over the nose during the climb When reaching the desired altitude the electric fuel pump may be tumed off 4 27 CRUISING The cruising speed of the Cherokee Archer is determined by many factors including power setting temperature loading and equipment installed in the airplane The normal maximum cruising power is 75 of the rated horsepower of the engine Airspeeds which may be obtained at various altitudes and power settings can be determined from the performance graphs provided by Section 5 Use of the mixture control in cruising flight reduces fuel consumption significantly especially at higher altitudes The mixture should be leaned during cruising operation above 5000 ft altitude and at pilot s discretion at lower altitudes when 75 power or less is being used If any doubt exists as to the amount of power being used the mixture should be in the full RICH position for all operations under 5000 feet To lean the mixtur
205. se back on the control wheel as required to moothly regain a level flight attitude VB 790 ISSUED JUNE 18 1976 10 PIPER AIRCRAFT CORPO ION SECTION 3 28 181 CHEROKEE ARCHER EMERGENCY PROCEDURES 3 27 OPEN DOOR The cabin door on the Cherokee is double latched so the chances of its springing open in flight at both the top and side are remote However should you forget the upper latch or not fully engage the side latch the door may spring partially open This will usually happen at takeoff or soon afterward partially open door will not affect normal flight characteristics and a normal landing can be made with the door open If both upper and side latches are open the door will trail slightly open and airspeed will be reduced slightly To close the door in flight slow the airplane to 87 KIAS close the cabin vents and open the storm w w If the top latch is open latch it If the side latch is open pull on the armrest while moving the la to the latched position If both latches are open close the side latch then the top latch 3 28 CARBURETOR ICING Under certain moist atmospheric conditions at temperatures of 5 C to 20 C it is possible form in the induction system even in summer weather This is due to the high air velocity through the carburetor venturi and the absorption of heat from this air by vaporization of the fuel To avoid this carburetor preheat is
206. set Piper Dwg 68856 10 Cert Basis TC 2A13 0 5 60 0 30 ISSUED JULY 12 1977 REPORT VB 790 REVISED APRIL 13 1979 Suppl Chpt6 Diamond Mass and Balance Equipment List MAINTENANCE Reg OE DKT Type PA28 181 S N 28 7890244 PIPER Date 22 02 06 Cert EODM 101 EMZ No RC SA1122 conj with FAA STC SA00705WI Description Type _____ SIN inst iAudio Panel 40 1 0 A 96274173 _ ET 2B 7 27 1066 10 X Antenna KA44B x RR ____ DM C70 4 FA Atitude Gyro 7 __ _______ X 1003 003423 x Antenna Coupler _____ 7 COMMINAVIGPS armin x GPS Antenna 616 001 82 X 16 013 00049 01 7 05 10664 X Vou 2 2 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 181 CHEROKEE ARCHER II WEIGHT AND BALANCE n Miscellaneous Optional Equipment Item Mark if Weight Arm Moment No Item Instl Pounds Aft Datum Lb In 321 Zinc Chromate Finish Basis 2 13 gt 5 0 158 0 790 323 Stainless Steel Control Cables Cert Basis TC 2A13 325 Air Conditioner Piper Dwg 99575 3 Cert Basis TC 2A13 P 68 3 103 6 7076 327 Overhead
207. t is recommended that engine oil be drained and renewed every 50 hours The oil filter element should be changed every 56 hours of operation The interval between oil and oil filter changes should not exceed a total of four 4 months Under unfavorable dusty conditions the oil and oil filter should be changed more frequently It is recommended that single or multi viscosity aviation grade oils in accordance with latest issue of Textron Lycoming Service Instruction 1014 be used The following seasonal aviation oil grades and seasonal ambient temperature ranges are recommended Average Ambient MIL L 6082B MIL L 22851 Air Temperature Mineral Ashless Dispersant For Starting SAE Grade SAE Grades All Temperatures 15W 50 or 20W 50 Above 80 F 60 60 Above 60 F 50 40 or 50 30 F to 90 F 40 40 O F to 70 F 30 30 40 or 20W 40 O F to 90 20W 50 20W 50 or 15 W 50 Below 10 F 20 30 or 20W 30 When operating temperatures overlap indicated ranges use the lighter grade oil NOTE Refer to the latest issue of Textron Lycoming Service Instruction 1014 Lubricating Oil Recommendations for further information 8 21 FUEL SYSTEM a Servicing Fuel System Refer to the PA 28 Cherokee Service Manual and Periodic Inspection Report for fuel system servicing and inspection b Fuel Requirements AVGAS ONLY Aviation grade fuel with a minimum octane of 100 130 must be used in this airplane Since the use of lower grades can cause serious damage in a sh
208. tch LATCH BEFORE FLIGHT On inside of the baggage compartment door BAGGAGE MAXIMUM 200 LBS UTILITY CATEGORY OPERATION NO BAGGAGE OR AFT PASSENGERS ALLOWED NORMAL CATEGORY OPERATION SEE PILOT S OPERATING HANDBOOK WEIGHT AND BALANCE SECTION FOR BAGGAGE AND AFT PASSENGER LIMITATIONS In full view of the pilot MANEUVERING SPEED 113 KIAS AT 2550 LBS SEE P O H UTILITY CATEGORY OPERATION NO AFT PASSENGERS ALLOWED DEMONSTRATED CROSS WIND COMPONENT 17 KTS On the instrument panel in full view of the pilot when the oil cooler winterization kit is installed COOLER WINTERIZATION PLATE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50 F In full view of the pilot UTILITY CATEGORY OPERATION ONLY 1 NO AFT PASSENGERS ALLOWED 2 ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING ENTRY SPEED SPINS PROHIBITED STEEP TURNS 113 5 LAZY EIGHTS 113 KIAS CHANDELLES 113 KIAS On the instrument panel in full view of the pilot WARNING TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT THROUGH CLOUD FOG OR HAZE REPORT 790 ISSUED JUNE 18 1976 2 8 SECTION 3 EMERGENCY PROCEDURES Paragraph 1 3 1 Generale T m T HELM 3 3 Emergency Procedures Check 1481 Engine Fire During SD DEM MERE RECURSUS
209. tching primer and finished with acrylic lacquer REPORT VB 790 ISSUED JUNE 18 1976 7 22 REVISED MARCH 30 1984 PIPER AIRCRAFT CORPORATION 4 7 28 181 CHEROKEE ARCHER DESCRIPTION AND OPERATION D 1 7 33 AIR CONDITIONING The air conditioning system is a recirculating air system The major items include evaporator condenser compressor blower switches and temperature controls The evaporator is located behind the left rear side of the baggage compartment This cools the air that is used for air conditioning The condenser is mounted on a retractable scoop located on the bottom of the fuselage and to the rear of the baggage compartment area The scoop extends when the air conditioner is and retracts toa flush position when the system is OFF The compressor is mounted on the forward right underside of the engine It has an electric clutch ch automatically engages or disengages the compressor to the belt drive of the compressor electrical blower is mounted on the aft side of the rear cabin panel Air from the baggage area is drawn through the evaporator by the blower and distributed through an overhead duct to individual outlets located adjacent to each occupant The switches and temperature control are located on the lower right side of the instrument panel in the climate control center panel The temperature control regulates the desired temperature of the cabin Turn the cont
210. ted from adverse weather conditions and that it presents no danger to other aircraft When parking the airplane for any length of time or overnight it is suggested that it be moored securely 1 To park the airplane head it into the wind if possible 2 Set the parking brake by pulling back on the brake lever and depressing the knob on the handle To release the parking brake pull back on the handle until the catch disengages then allow the handle to swing forward CAUTION Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze a brake 3 Aileron and stabilator controls should be secured with the front seat belt and chocks used to properly block the wheels d Mooring The airplane should be moored for immovability security and protection The following procedures should be used for the proper mooring of the airplane 1 Head the airplane into the wind if possible 2 Retract the flaps 3 Immobilize the ailerons and stabilator by looping the seat belt through the control wheel and pulling it snug 4 Block the wheels 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 material leave sufficient slack to avoid damage to the airplane should the contract CAUTION Use bowline knots square knots or locked slip knots Do not use plain
211. tensity is controlled by the instrument lights potentiometer Ti ANT ADF MODE ANNUNCIATOR Antenna ANT is selected by the out position of the ADF button This mode improves the audio reception and is AFM M26 Rev 29 Nov 2005 Diamond MAINTENANCE Doc No AFM M26 KR87 usually used for station identification The bearing pointer is deactivated and will park in the 90 relative position Automatic Direction Finder ADF mode is selected by the depressed position of the ADF button This mode activates the bearing pointer The bearing pointer will point in the direction of the station relative to the airplane heading 2 IN USE FREQUENCY DISPLAY The frequency to which the ADF is tuned is displayed here The active ADF frequency can be changed directly when either of the timer functions is selected 3 BFO Beat Frequency Oscillator ANNUNCIATOR The BFO mode activated and annunciated when the BFO button is depressed permits the carrier wave and associated morse code identifier broadcast on the carrier wave to be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of signal is not used in the United States air navigation It is used in some other countries and marine beacon 4 STANDBY FREQUENCY FLIGHT TIME OR ELAPSED TIME ANNUNCIATION When FRQ is displayed the STANDBY frequency is displayed in the right hand display The STANDBY frequency is s
212. ter switch should be returned to the position after the checks are complete visual check of the fuel tank quantity should be performed Remove the filler cap from each tank and visually check the supply and color Be sure to secure the caps properly after the check is complete The fuel system sumps and strainer should be drained daily prior to the first flight and after refueling to avoid the accurnulation of contaminants such as water or sediment Each fuel tank is equipped with an individual quick drain located at the lower inboard rear comer of the tank The fuel strainer is equipped quick drain located on the front lower comer of the firewall Each of the fuel tank sumps should be d 4 first Then the fuel strainer should be drained twice once with the fuel selector valve on each tank Eacn time fuel is drained sufficient fuel should be allowed to flow to ensure removal of contaminants This fuel should be collected in a suitable container examined for contaminants and then discarded CAUTION When draining any amount of fuel care should be taken to ensure that no fire hazard exists before starting the engine Each quick drain should be checked after closing it to make sure it has closed completely and is not leaking ISSUED JUNE 18 1976 REPORT VB 790 REVISED JANUARY 20 1977 4 7 PIPER AFT CORPORATION SECTION 4 NORMAL PROCEDURES 28 181 vd EROKEE ARCHER II Check all of the fuel tank vents t
213. th Regular Tube Cert Basis TSO C62 REVISED JANUARY 20 1977 Moment Lb 1n 133 REPORT VB 790 6 21 6 PIPER CORPORATION VEIGHT AND BALA PA 28 181 CHEROKEE ARCHER u ET THIS PAGE INTENTIONALLY LEFT BLANK REPORT 790 JSSUED JUNE 18 1976 6 22 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 181 CHEROKEE ARGHER II Wa AND BALANCE d Electrical Equipment Item Mark if Weight Arm In Moment No tem Instl Pounds Aft Datum Lb In ISSUED JUNE 18 1976 REPORT VB 790 6 23 6 PIPER AIRCRAFT CORPORATION EIGHT AND BALAN PA 28 181 CHEROKEE ARCHER THIS PAGE INTENTIONALLY LEFT BLANK ORT VB 790 ISSUED JUNE 18 1976 PIPER AIRCRAFT CORPORATION SECTION PA 28 181 CHEROKEE ARCHER II WraGHT AND BALANC e Instruments Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In 53 Airspeed Indicator Piper PS50049 308 Cert Basis TSO C2b 55 Altimeter Piper Spec PS50008 2 or 3 Cert Basis TSO C10b 57 Compass Cert Basisz TSO C7c ISSUED JUNE 18 1976 REPORT VB 790 6 25 CTION 6 PIPER AIRCRAFT CORPORATION IGHT AND BALANC PA 28 181 CHEROKEE ARCHER II THIS PAGE INTENTIONALLY LEFT BLANK VB 790 ISSUED JUNE 18 1976 PIPER AIRCRAFT CORPORATION SECTION 6 28 181 CHEROKEE ARCHER II AND BALANC
214. that the nose wheel is in line with the fore and aft axis of the plane when the rudder pedals and rudder are centered Alignment of the nose wheel can be checked by pushing the airplane back and forth with the rudder centered to determine that the plane follows a perfr straight line The turning arc of the nose wheel is 30 0 2 in either direction and is limited by stops the bottom of the forging The rudder pedal arm stops should be carefully adjusted so that the pedal arms contact the stops just after the rudder hits its stops This guarantees that the rudder will be allowed to move through its full travel REPORT 790 ISSUED JUNE 18 1976 8 10 PIPER AIRCRAFT CORPORATION SECTION PA 28 181 CHEROKEE ARCHER HANDLING SERVICING AND MAINTENANCE 8 17 PROPELLER SERVICE The spinner and backing plate should be frequently cleaned and inspected for cracks Before eacl flight the propeller should be inspected for nicks scratches and corrosion If found they should be repaired as soon as possible by a rated mechanic since a nick or scratch causes an area of increased stres which can lead to serious cracks or the loss of a propeller tip The back face of the blades should be paintec when necessary with flat black paint to retard glare To pr vent corrosion the surface should be cleanec and waxed periodically 8 19 OIL REQUIREMENTS The oil capacity of the engine is 8 quarts and the minimum safe quantity is 2 quarts I
215. the airplane when the Audio Panel GMA 340 is installed The information contained within this Supplement is lo be used in conjunction with the complete AFM This Supplement is a permanent part of this AFM and must remain in this AFM at all times when the GMA 340 is installed 2 LIMITATIONS No change 3 EMERGENCY PROCEDURES A failsafe circuit connects the pilot s headset and microphone directly to COM 1 in case the power is interrupted or the unit is turned off 4A NORMAL PROCEDURES No change 4B ABNORMAL PROCEDURES No change 5 PERFORMANCE No change 6 MASS AND BALANCE Upon removal or installation of the GMA 340 the change of empty mass and corresponding center of gravity of the airplane must be recorded according to Chapter 6 of the Airplane Flight Manual 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7 14 AVIONICS AFM M10 06 2006 4 Diamond Doc No AFM M10 340 2 3 69 969 66 DELE 2923 109 amp HI 2 j 8 SB p p ju 47 SENS E E ta 5 OM 44 0902 40605 7 ORERATION FRONT PANEL CONTROLS Marker Beacon Lamps Marker Beacon Receiver Audio Select Mute Button Marker Beacon Receiver Sensitivity Indicator LED s Marker Beacon Receiver Sensitivity Selection Button Unit On Off Pilot Intercom System ICS Volume Pil
216. tion If sufficient runway remains to complete a normal landing land straight ahead 1f insufficient runway remains maintain a safe airspeed and make only a shallow turn if necessary to avoid obstructions Use of flaps depends on the circumstances Normally flaps should be fully extended for touchdown f sufficient altitude has been gained to attempt a restart maintain a safe airspeed and switch the fuel selector to another tank containing fuel Check the electric fuel pump to insure that it is ON and that the mixture is RICH The carburetor heat should be ON and the primer checked to insure that it is locked If engine failure was caused by fuel exhaustion power will not be regained after switching fuel tanks the empty fuel lines are filled This may require up to ten seconds If power is not regained proceed with the Power Off Landing procedure refer to the emergency check list and paragraph 3 13 ISSUED JUNE 18 1976 REPORT VB 790 3 7 REVISED JULY 3 1978 PIPERA RAFT CORPORATION SECTION 3 HEROKEE ARCHER EMERGENCY PROCEDURES 28 1 311 ENGINE POWER LOSS IN FLIGHT flow interruption and power will be restored Complete engine power loss is usually caused by fuel for an shortly after fuel flow is restored If power loss occurs at a low altitude the first step is to p emergency landing refer to paragraph 3 13 An airspeed of at least 76 KIAS should be maintained I
217. tional Airspace System in accordance with AC 20 138 of the approved sensors for a single or dual GNS 430 installation for North Atlantic Minimum Navigation Performance Specification MNPS Airspace in accordance with AC 91 49 and AC 120 33 systems meets RNPS airspace requirements of AC 90 96 and in accordance with AC 20 138 and JAA AMJ 20X2 Leaflet 2 Revision provided it is receiving usable navigation information from the GPS receiver PIPER PA32 190 00140 03 Rev C FAA APPROVED Page 4 of 10 DATE 11 21 02 amp GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum Navigation data is based upon use of only the Global Positioning System GPS operated by the United States of America SECTION LIMITATIONS 1 The GARMIN GNS 430 Pilot s Guide P N 190 00140 00 Rev dated October 1998 or ater appropriate revision must be immediately available to the flight crew whenever navigation is predicated on the use of the system In addition to the Pilot s Guide the appropriate Pilot s Guide Addendum also must be immediately available to the flight crew for lightning detection and traffic information service TIS equipment interfaced to the system 2 The GNS 430 must
218. tional tolerance permitted Serial nos 28 7790001 through 28 7790607 nos 28 7890001 and up REPORT YB 790 1 2 PIPER CORPORATION 28 181 EROKEE ARCHER IAS 154 KTS 125 KTS to 154 KTS 55 KTS to 125 KTS 49 KTS to 102 KTS 1 Lycoming 0360 A4A or 0 360 A4M with carburetor setting 10 3878 180 2700 245 F 25 PSI 90 PSI 5 PSI 8 PSI 100 130 1 Sensenich 76 8 5 0 60 or 76EM8S5 0 62 76 IN 76 IN Not above 2425 Not below 2325 RPM Not above 2375 RPM Not below 2275 RPM ISSUED JUNE 18 1976 REVISED MARCH 30 1984 PIPER AIRCRAFT CORPO TION PA 28 181 CHEROKEE ERII SECTION 2 LIMITATIONS 2 9 POWER PLANT INSTRUMENT MARKINGS a Tachometer Green Arc Normal Operating Range Red Line Maximum Continuous Power b Oil Temperature Green Arc Normal Operating Range Red Line Maximum c Pressure Green Arc Normal Operating Range Yellow Arc Caution Range Idle Red Line Minimum Red Line Maximum d Fuel Pressure Green Arc Normal Operating Range Red Line Minimum Red Line Maximum 2 11 WEIGHT LIMITS a Maximum Weight b Maximum Refer to Section 5 Performance for maximum by performance ISSUED JUNE 18 1976 REVISED MAY 23 1980 NOTE 500 to 2
219. tions are of symbols abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot a General Airspeed Terminology and Symbols CAS Calibrated Airspeed means the indicated speed of an aircraft corrected for position and instrument error Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level KCAS Calibrated Airspeed expressed in Knots GS Ground Speed is the speed of an airplane relative to the ground IAS Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error 1 values published in this handbook assume zero instrument error KIAS Indicated Airspeed expressed in Knots M Mach Number is the ratio of true airspeed to the speed of sound TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude temperature and compressability VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane MEE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNE MNE Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time VNO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution Stalling Spee
220. tor is located behind the instrument panel and is accessible from below the instrument panel REPORT VB 790 ISSUED JUNE 18 1976 7 15 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND PA 28 181 CHEROKEE ARCHER II 7 19 INSTRUMENT PANEL The instrument panel Figure 7 15 of the Cherokee is designed to accommodate the customary advanced flight instruments and the normally required power plant instruments The artificial horizon and directional gyro are vacuum operated through use of a vacuum pump installed on the engine while the turn and bank instrument is electrically operated A vacuum gauge is mounted on the far right side of the instrument panel The radios and circuit breakers are on the right hand instrument panel Extra circuits are provided for the addition of optional radio equipment An annunciator panel 35 mounted in the upper instrument panel to wam the pilot of a possible malfunction in the alternator pressure or vacuum systems REPORT VB 790 ISSUED JUNE 18 1976 7 16 9061 81 INNT 830551 Sil angry 4 LNAWNYISNI 15 17 1813 20 NS 53 lt 2525 2 32 ISLI SC Yd 06 LUOITU LEL TURN INDICATOR AIRSPEED INDICATOR DIRECTIONAL GYRO ATTITUDE GYRO VERTICAL SPEED INDICATOR ALTIMETER ANNUNCIATOR PANEL MAGNETIC COMPASS OMNI GLIDE SLOPE INDICATORS
221. ubes as possible Lines should be long enough to clear the nose and or tail by not less than fifteen feet and a qualified person should ride in the pilot s seat to maintain control by use of the brakes Taxiing Before attempting to taxi the airplane ground personnel should be instructed and approved by a qualified person authorized by the owner Engine starting and shut down procedures as well as taxi techniques should be covered When it is ascertained that the propeller back blast and taxi areas are clear power should be applied to start the taxi roll and the following checks should be performed 1 Taxia few feet forward and apply the brakes to determine their effectiveness 2 While taxiing make slight turns to ascertain the effectiveness of the steering 3 Observe wing clearance when taxiing near buildings or other stationary objects If possible station an observer outside the 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 material that may cause damage to the propeller blades ISSUED JUNE 18 1976 PIPER AIRCRAFT CORPORATION SECTION 8 PA 28 181 CHEROKEE ARCHER II HANDLING SERVICING AND MAINTENANCE c Parking When parking the airplane be sure that it is sufficiently protec
222. ulilize the following or later FAA approved software versions COMM a The Main software version is disptayed on the GNS 430 self test page immediately after tum on for 5 scconds The remaining system software versions can be verified on the AUX group sub page 2 SOFTWARE DATABASE VER IFR enroute and terminal navigation predicated upon the GNS 430 5 GPS Receiver is prohibited unless tho pilot verifies the currency of the data base or verifies each selected waypoint for accuracy by reference to current approved data PIPER PA32 FAA APPROVED 190 00140 03 Rev DATE 11 21 02 Page 5 of 10 4 GARMIN International Inc 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN GNS 430 VHF COMMUNICATION TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER Instrument approach navigation predicated upon the GNS 430 s GPS Receiver must be accomplished in accordance wilh approved instrument approach procedures that are retrieved from the GPS equipment data base The GPS equipment database must incorporate the current update cycle 4 Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Jntegrity Monitoring RAIM must bo available at the Final Approach Fix Accomplishment of ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for GPS overlay with the GNS
223. um Lb In 87 King KX 170 VHF Comm Nav a Transceiver Single 5 7 5 56 6 425 b Transceiver Dual 15 0 56 6 849 Cert Basis TC 2A13 89 King KX 1795 VHF a Transceiver 9 4 56 6 532 b King KN 72 VOR LOC Converter NEN 1 3 183 6 239 c King KN 73 Glide Slope Receiver 32 184 3 590 d King KN 75 Glide Slope Receiver pH 1 6 184 3 295 e King KN 77 VOR LOC Converter 3 6 183 6 661 f King KI 204 VOR ILS Indicator 17 60 5 103 King 520 VOR ILS Indicator c 2 8 60 5 169 Cert Basis TSO C36c C375 C38b 9 King KX 175 VHF a Transceiver 2nd 8 6 56 6 487 b King 72 VOR LOC Converter Ep 1 3 183 6 239 c King KN 77 VOR LOC Converter 4 2 183 6 771 d King 203 VOR ILS Indicator l 1 6 60 5 97 e King KNI 520 VOR ILS Indicator ER 2 8 60 5 169 Cert Basis TSO C36c C37b C38b C40a ISSUED JUNE 18 1976 VB 790 REVISED MAY 23 1980 42 PIPER AIRCRAFT CORPORATION SECTION 6 28 181 CHEROKEE ARCHER II AND BALANCE m Radio Equipment Optional Equipment cont Item Mark if Weight Amn In Moment No Item Instl Pounds Aft Datum Lb In 193 King KI 201 VOR LOC Ind a Single 2 5 59 6 149 b Dual 5 0 59 9 300 Cert Basis 2A13 194 King 208 VOR LOC Indicator a Single EUER 1 0 59 6 60 b Dual 2 0 59 9 120 Cert Basis TSO C34c C36c 40 195 King K1 209 VOR L
224. um xe STRIP adjust Oikpressune STARTING ENGINE WHEN FLOODED Throttle iu Lxx RE open full M ster switch ou are ON Electricfuelpump 4 OFF Mixture M bes idle cut off Starlet d ie engage poh eee advance Tiroler retard Ollpressur un bok bk A qe S check REPORT VB 790 44 STARTING WITH EXTERNAL POWER SOURCE Master switch mex electrical equipment Terminals aE connect External power plug insert in fuselage Proceed with normal start Throttle lowest possible RPM External power pug disconnect from fuseluge Masterswitch ON check ammeter pressures ot a rete Sud check WARM UP Throttle sesar are 800 to 1200 RPM TAXIING removed M der peers clear Throttle uw eR RIS apply slowly Brakes ew ue SS check Steering vete tec teg o n A dew s check GROUND CHECK Throttle sense cemere t 2000 RPM Magnel s wepip adai 175 diff 50 RPM Vacuums vo uno eur ee 5 0 Hg Oil temp EEE tenta check llipressure 2 49693 Air conditlorier 22 U
225. umentenbrett im direkten Blickfeld des Piloten ist folgendes Hinweisschild anzubringen Kopie Normalverfahren Normal Procedures Star und Landung auf Tank rechts durchf hren wenn Autobenzin oder ein Tankwahlschalter Gemisch aus Autobenzin und AVGAS 100 LL verwendet wird Kraftstoff Planung Die Tankwahlschaltung soll so gew hlt werden dass bei Verwendung von Auto Benzin und einer Aussentemperatur OAT von mehr als 30 ein Krafstorf Vorrat von mindestens des Beh ltervolumens f r den normalen Betrieb verbleibt Kraftstoff Zusatz Es sind 2 elektrisch betriebene Zusatzpumpen nr 1 und Nr 2 eingebaut pumpen die durch Schalter Instrumentenbrett eingeschaltet werden bei Rollen Start Steigflug oder Landung einge Eine dieser Pumpen muss ausreichender schaltet sein Schaller ON W hrend des Reisefluges Krafistofdruck vorausgesetzt kann diese Pumpe ausgeschaltet werden Schalterstellung OFF Vgl auch Beschr nkungen Limitations im Originalhandbuch des Flugzeuges Zur gleichm ssigen Nutzung der Pumpen im Interesse der Belriebssicherheit wird die wechselweise Varwendung der Pumpen empfohlen Funktionskontrolle Batterie Hauptschalter einschalten und die Pumpen Nr 1 und Nr 2 nacheinancer der Pumpen vor einschalten Jeweils Funktion durch H ren des Pumpenlaufger usches und des dem Anlassen Kraftstoffdruckes jeder Pumpe berpr fen Pumpe wieder ausschalten Notverfahren E
226. ust Oil pressure STARTING ENGINE WHEN LOODED Throttle open full Master switch nm n n ON Electric fuel pump OFF idle cut off 225 om oO etit per IS Mixture er ae advance Throttle retard Dil pressure check REPORT VB 790 44 PIPERAI CORPORATION 28 181 dEROKEE ARCHER STARTING WITH EXTERNAL POWER SOURCE Master switch ooro OFF All electrical equipment OFF Terminals nt m m mmt connect External power pug 3 insert in fuselage Proceed with normal start lowest possible Throttle RPM External power plug disconnect from fuselage Master switch ON check ammeter Oil pressure ch WARM UP Throttle 800 to 1200 RPM TAXIING Chocks m t n m Im removed n m meet tnt clear Throttle apply slowly Brakes check Steering m tmt check GROUND CHECK Throttle 2000 Magnetos 175 diff 50 RPM Vacuum ee t m f 5 0 Hg 1 Oil temp check pressure t nt tnnt n check Air conditioner check Annunciator panel press to test Carbu
227. ven spins and spin recovery becomes more difficultas the center of gravity moves aft of the approved limit properly loaded airplane however will perform as intended Before the airplane is licensed a basic empty weight and location is computed basic empty weight consists of the standard empty weight of the airplane plus the optionalequipment Usingthe basicempty weight and C G location the pilot can determine the weight and C G position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope The basic empty weight and location are recorded in the Weight and Balance Data Form Figure 6 5 and the Weight and Balance Record Figure 6 7 The current values should always be used Whenever new equipment is added or any modification work is done the mechanic responsible for the work is required to compute a new basic empty weight and C G position and to write these in the Aircraft Log Book and the Weight and Balance Record The owner should make sure that it is done weight and balance calculation is necessary in determining how much fuel or baggage can be boarded so as to keep within allowable limits Check calculations prior to adding fuel to insure against improper g The following pages are forms used in weighing an airplane and in computing basic empty weight position and useful load Note that the useful load includes usable fuel
228. y loose material that may cause damage to the propeller blades TAXIING Before attempting to taxi the airplane ground personnel should be instructed and approved by a qualified person authorized by the owner Ascertain that the propeller back blast and taxi areas are clear Power should be applied slowly to start the taxi roll Taxi a few feet forward and apply the brakes to determine their effectiveness While taxiing slight turns to ascertain the effectiveness of the steering Observe wing clearances when taxiing near buildings or other stationary objects If possible station an Observer outside the airplane Avoid holes and ruts when taxiing over uneven ground Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones gravel or any loose material that may cause damage to the propeller blades 4 19 GROUND CHECK The magnetos should be checked at 2000 RPM Drop off on either magneto should not exceed 175 RPM and the difference between the magnetos should not exceed 50 RPM Operation on one magneto should not exceed 10 seconds Check the vacuum gauge the indicator should read 5 0 1 Hg at 2000 RPM Check the annunciator panel lights with the press to test button Also check the air conditioner carburetor heat should also be checked prior to takeoff to be sure the control is operating properly and to clear any ice which may have formed during taxiing Avoid prolonged ground ope

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