cherol-lee ARCHER PILOT'S OPERATING MANUAL

The stabilator provides extra stability and controllability with less size, drag and weight than conventional tail surfaces. The ailerons are provided with a differential action which tends to reduce adverse yaw in turning maneuvers, and which also reduces the amount of coordination required in normal turns. A rudder trim adjustment is mounted on the right side of the pedestal below the throttle quadrant and permits directional trim as needed in flight. The flaps are manually operated, balanced for light operating forces and spring-loaded to return to th e up position. A past-center lock incorporated in the actuating linkage holds the flap when it is in the up position so that it may be used as a 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 us ed as a step. The flaps have three extended positions, l 0, 25 and 40 degrees. 2-4 AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 • • ··. ~ . -~-. \ AIRPLANE AND SYSTEMS ISSUED : JULY 9, 1973 CHEROKEE ARCHER Throttle Quadrant and Console 2-5 CHEROKEE ARCHER ----------------·-----·------------------- -; - . . . . ~ - _: .:;. :-- ::: .- -· ,_ ---- Fuel Selector FUEL SYSTEM Fuel is stored in two twenty-five gallon (24 gallons usuable) tanks which are secured to the leading edge structure of each wing by screws and nut plates. This allows easy removal for service or inspection. TI1e fuel selector control 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. Each ta nk has an individual quick drain located at the bottom , inboard rear comer , and should be drained to check for water before each flight (a special c ontain er is furnished for this operation). The fuel strainer, which is also equipped with a quick drain, is located on the front lower left corner of the fire wall. This strainer should be drained regularly to check for water or sedime nt accumulation. To drain the lines from the tanks, the tank selector valve must be switched to each tank in turn, with th e electric pump on , and the gascolator drain valve opened. (Refer to th e Handling and Servicing Section for the complete procedure.) Fuel quantity and pressure are indicated on gauges located in a cluster on the left side of the instrument panel. An optional engine priming system is available to facilitate starting. The primer pump is located to the immediate left of the throttle quadrant. 2-{) AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 FUEL QUANTITY GAUGES FUEL TANK SELECTOR VALVE MAIN TANK AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 FUEL PRESSURE GAUGE CARBURETOR Fuel System Schematic CHEROKEE ARCHER MAIN TANK ENGINE FUEL PUMP ELECTRIC FUEL PUMP 2-7 WARNING when flying through overcast ...,.,.,., .... '"""'""" light can spacial msonem.anon. close proximity to ground, during ' 4master switch.,. hereafter this manual both the "'BAT" alternator side "ALT" are to be depressed simultaneously to OFF or ON as directed. nos. 7505001 and up AIRPLANE AND SYSTEMS REVISED: MARCH 26, 1979 CHEROKEE ARCHER 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 maximum 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 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 ammeter during flight, reduce the electrical load by turning off all unnecessary electrical Check both 5 ampere field and 60 ampere output breaker and reset if open. If neither circuit breaker is open, tum off the "ALT" switch for 1 second to reset the overvoltage relay. If ammeter continues to indicate no output, maintain minimum electrical load and terminate flight as soon as practical. Maintenance on the alternator should prove to be a minor factor. Should service be required, contact the local Piper Dealer. AIRPLANE AND SYSTEMS REVISED: MAR CH 26, 1979 2-8a 2-9 AMMfTER SOURCE-POWER RELAY ENERGIZING CIRCUIT MASTER SWITCH .. ,....., ...u.:;u.vi and Starter Schematic (Ser. nos. 7405001 through 7405290) AIRPLANE AND SYSTEMS REVISED: JUNE 17, CHEROKEE ARCHER \ 2-10 ~· .\ ·\· \ .~ -. \ Circuit Breaker Panel AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 • • 5 6 20 21 22 23 24 25 26 27 I. STALL WARNING LIGHT 2. CLOCK 3. TURN INDICATOR 4. AIRSPEED INDICATOR ~. DIRECTIONAL GYRO 6. ATTITUDE GYRO 7 . VERTICAL SPEED INDICATOR 8 . ALTIMETER 9. TRANSPONDER 10. MARKER BEACON l l . MAGNETIC COMPASS 12. OMNI & GLIDE SLOPE INDICATORS 13 . AUDIO SELECTOR PANEL 14. UHFTRANSCEIVERS 28 11 l 0 41 13 29 30 3' J2 33 34 35 15 . ADF RECEIVER 16. DME RECEIVER 17. CIGAR LIGHTER 18. SUCTION GAUGE 19. HEAT& DEFROST CONTROL 20. MIKE JACK 2 I. PHONE JACK 2 2. AUTOPILOT 23. ENGINE INSTRUMENT CLUSTER 24. OMNI COUPLER 25. NAV SWITCH 26. MAGNETO& STARTER SWITCH 27 . PITCH CONTROL 28. CHECKLIST • 14 36 37 2 9 . 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 15 16 17 18 19 38 39 40 TACHOMETER FUEL GAUGES PRIMER MICROPHONE THROTTLE QUADRANT FRICTION LOCK CARBURETOR HEAT CONTROL EGT INDICATOR INSTRUMENT PANEL LIGHTS CIRCUIT BREAKER PANEL CIRCUIT BREAKER COVER CLIMATE CONTROL ANNUNCIATOR PANEL (SER . NOS. 7505001 AND UP) • AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 Pitot - Static System CHEROKEE ARCHER 2-13 CHEROKEE ARCHER PITOT-STATIC SYSTEM and water parked, a cover should head will give erratic or zero NOTE During the preflight, check to make sure the pitot cover is removed. HEATING AND VENTILATING SYSTEM ~ Heat the cabin interior and the defroster system is provided a heater muff attached to the exhaust system. 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 """"'"' .... L"''""' on top of the heat ducts next to the console. air inlets are located in leading of the wing at the mtersiect:ton A large adjustable outlet is located on the the cabin near the floor seat air outlets are as optional equipment. Air is exhausted outlet under the rear seat. A cabin air blower, incorporated in the system, vailable as optional equipment. An optional with a cabin air blower available on models without air conditioning. This blower is by a "FAN" switch with 4 positions - "OFF," "LOW," "MED," or "HIGH." 2-14 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. AIRPLANE AND SYSTEMS REVISED: MARCH 26, 1979 \ .... " ........... "' ,. " NM'<i'IJ)\Or-.OOO>O"""'N AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 \ \ \ Heating and Ventilating System CHEROKEE ARCHER / I 5 I L FAA F T NOTE H. W. BARNHOUSE PIPER AIRCRAFT CORPORATION D. 0. A. No. S0-1 VERO BEACH, FLORIDA DATE OF APPROVAL: MAY 14, 1973 APPROVAL BASIS: CAR 3 REPORT: VB-SSS MODEL: PA-28-180 I. J. TABLE CHEROKEE ARCHER CONTENTS . 3-iii . . . . . . . . . . . . . . . . . . . . 3-1 3-1 . . . . . . . . . . . . . . . . . . 3-1 3-2 3-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3 "",...,......... ,..,. .....",, Airplanes ...... ~ .... ~ ...... ~ . . . . . . . . 3-5 SECTION II Procedures SECTION III IV Optional ~4•-•.tP''u"'·'" . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 . . . . . . . . . . . . . 3-9 A. B. c. D. Trim Installation ........................ . 3-1 l 3-13 3-16 lI Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . Air Conditioner Installation Of FAA APPROVED MAY 14.1 REVISED: JANUARY 20, 1975 II AutoControl III and/or AutoControl IIIB . . . . . . 3-19 REPORT: VB-558 PAGE 3-i MODEL: PA-28-180 REPORT: VB-558 MODEL: PA-28-180 BLANK APPROVED MAY 14, 1973 AIRPLANE Revision Revised ,,(.. 3 4 Title 3-i 3-11 9, 3-21, 3-i 3-1 13 14 3-15 3-16 3-I 9 FAA APPROVED MAY 14, 1 REVISED: NOVEMBER 2L 1 REVISIONS R SECTION I LIMITATIONS CHEROKEE ARCHER following limitations must be observed in the operation of this airplane: A. ENGINE Lycoming 0-360-A4A or 0-360-A4M with carburetor setting I0-3878 ENGINE LIMITS For all operations 2700 RPM, 180 HP B. FUEL (AVGAS ONI Y) l 00/l 30 minimum octane aviation fuel C. PROPELLER Sensenich M76EMMS or 76EM8S5. Maximum diameter 76 inches, minimum 76 inches. Static RPM at maximum permissible throttle setting. Not over 2425, not under No additional tolerance permitted. D. POWERlNSTRUMENTS OIL TEMPERATURE Green Arc (Normal Operating Range) Red Line (Maximum) OIL PRESSURE Green Arc (Normal Operating Range) Yellow Arc (Caution Range) Red Line (Minimum) Red Line (Maximum) PRESSURE Green Arc (Normal Operating Range) Red Line (Minimum) Red Linc (Maximum) TACHOMETER Green Arc (Normal Operating Range) Red Line (Maximum Continuous Power) FAA APPROVED MAY 14, 1973 REVISED: MARCH 16. 1984 F to 60 PSI to 90 PSI PSI to 60 25 PSI 90 PSI .5 PSI to 8 PSI .5 PSI 8 PSI 500 to 2700 RPM 2700 RPM REPORT: VB-558 PAGE 3-1 MODEL: PA-28-180 to 140 MPH KTS to 1 l 61MPHtoll MPH ( KTS to 100 LBS 1950 LBS MAY 14, 1973