Pilot's Operating Manual

Airplane Performance. Added page. Added page. Revised item 6. Added PAC Approval Form. May 30, 1974 Added Applicability and Item HI. Original Pages Issued. Added Rev. 1 to Report: VB-558. Added Rev. 2 to Report: VB-547. (NOTE: AIRCRAFT DELIVERED WITH MANUALS PRIOR TO THIS REVISION DO NOT REQUIRE THIS REVISION.) Added Annunciator Panel information and June 17, 1974 footnote. Added page (added material from page 2-8). Relocated page (Alternator-Starter Schematic). Added page (Altemator-Starier Schemadc). Added Annunciator Panel information and footnote. Revised Instrument Panel illustration. Added Seat Removal mstructions. Added Rev. 2 to Report: VB-558. Added Rev. 3 to Report: VB-547. Added Annunciator Panel check to Warm- up and Ground Check; added footnote. Revised item 6; added footnote. Relocated material from page 8-1. IV PILOT'S OPERATING MANUAL LOG OF REVISIONS (cent) Revision Rev. 3 (cont) Rev. 4 - 761 556 (PR750120) Rev. 5-761 556 (PR751121) Rev. 6-761 556 (PR790326) Revised Pages 9-i 9-2 9-3 9-4 9-5 9-6 9-7 9-8 9-9 9-10 10-11 1-2 2-1 AF/M W/B 7-4 7-8 8-2 10-8 Ill 1-1 1-2 2-1 AF/M W/B 8-1 9-4 9-6 2-8 2-8a 2-14 W/B 7-2 7-8, 7-9 Description Revised Performance Charts Index. Revised Takeoff Chart. Revised Climb Chart. Revised Range Chart. Revised Engine Chart. Revised Airspeed Chart Revised Stall Speed vs Weight Chart. Revised Stall Speed vs Angle of Bank Chart. Revised Glide Chart. Revised Landing Chart. Revised Battery Service. Added 0-360-A4M engine designation and footnote. Added 0-360-A4M engine designation and footnote. Added Rev. 3 to Report: VB-558. Added Rev. 4 to Report: VB-547. Added new item 9. ; revised existingitem nos. under TAKEOFF. Revised ELT info. Added item 11. AddedO-360-A4M engine designation under Oil Requirements. Added concluding ser. no. to Applicability. Revised Cruise Speed and Range figures;" revised Empty Weight and Useful Load; deleted footnote. Deleted footnote. Revised Airframe info; deleted footnote. Added Rev. 4 to Report: VB-558. Added Rev. 5 to Report: VB-547. Revised item 8 (Fuel Warning Tip). Revised Cruise Performance^ Range chart. Revised Cmise Performance - True' Airspeed chart. Added Warning. Added info. Added Caution. Added Rev. 6 to Report: VB-547. Revised items. Revised ELT info. Date Jan. 20, 1975 Nov. 21, 1975 March 26, 1979 iv-a PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont) Revision Rev. 7 - 761 556 (PR840316) Rev. 8 - 761 556 (PR900320) Revised Pages 1-2 2-16 AF/M W/B 7-1 7-4 9-i 10-1 10-9 10-11 10-12, 10-13 10-7 10-8 10-11, 10-12 10-13 Description Revised fuel and oil. Revised para. Added Rev. 5 to Report VB-558. Added Rev. 7 to Report VB-547 Added to preflight. Added to text info. Added Warning. Added to text info. Added text info. Revised para. Revised preventive maintenance info. Relocated info. from p. 10-8. Moved info. to p. 10-7. Revised para. Revised para. Revised para. Date March 16, 1984 March 20, 1990 iv-b TABLE OF CONTENTS GENERAL SPECIFICATIONS DESCRIPTION - AIRPLANE AND SYSTEMS AIRPLANE FLIGHT MANUAL F. A.A. APPROVED EMERGENCY PROCEDURES F. A. A. APPROVED EMERGENCY PROCEDURES WEIGHT AND BALANCE LOADING INSTRUCTIONS OPERATING INSTRUCTIONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SERVICING BLANK PAGE GENERAL SPECIFICATIONS Performance Weights ................................................ ^'" """""""""""""""""""""""""""""•"""•• ••"••"•••- i~\ Power Plant ............................................ _.... —--—-•• ••-•• •• •• •• •• •• •• ••-.......................... ^-^i Fuel and Oil................................... , --—---•• •• •• •• •• •• •• •• ••-......................................... i^ 1-2 Dimensions Landing Gear 1-2 1-2 1-i BLANK PAGE CHEROKEE ARCHER GENERAL SPECIFICATIONS PERFORMANCE , :pub shed flgures are for. standard airplanes flown at gross weight under standard londitions. atsea.leve1' unless otherwise stated. Performance foTaspecifira irpTane from^pubhshed. figures dePending UPOn the equipment installed, -Ae"condirio"n of ^nginej, l!anliand. eqmpment' atmosPheric conditions and piloting technique. Each'performan'ce is subject to the same conditions as on the'corresponding performance chartfrom it is taken in the Performance Charts Section. Takeoff Ground Run, 25° flaps, sea level (ft) Takeoff Distance Over 50-ft Obstacle, 25° flaps, sea level (ft) Best Rate of Climb Speed (mph) Rate of Climb (ft per min) Best Angle of Climb Speed, sea level (mph) Max Speed, sea level (mph) Max Speed Optimum Altitude 9300 ft., 75% Service Ceiling (ft) Absolute Ceiling (ft) Cruise Speed at best power mixture (mph) 65% power, 12, 800ft 60% power, 14,000 ft Range at best power mixture (mi)** 75% power, 9300 ft 65% power, 12, 800 ft Cruise speed at best economy mixture (mph) 75% power, 9300 ft 65% power, 12, 600 ft Range at best economy mixture (mi)** 75% power, 9300 ft 65% power, 12,600ft Stalling Speed, Haps down (CAS) (mph) Stalling Speed, flaps up (CAS) (mph) Landing Roll, sea level, flaps down (ft) Landing Distance Over 50-ft Obstacle, sea level (ft) 720 1625 85 725 76 148* 141* 14, 150 16, 500 132* 125* 645 705 131* 123* 715 774 61 68 635 1185 * All speeds stated are with optional wheel fairings installed. Subtract 3 mph ifwheel fairir are not installed. ** No reserve. WEIGHTS Gross Weight (Ibs) Standard Empty Weight (Ibs) Maximum Useful Load (Ibs) 2450 1404 1046 GENERAL SPECIFICATIONS REVISED: NOVEMBER 21, 1975 1-1 CHEROKEE ARCHER POWER PLANT Engine (Lycoming) Rated Horsepower Rated Speed (rpm) Bore (inches) Stroke (inches) Displacement (cubic inches) Compression Ratio Dry Weight (pounds) Propeller FUEL AVGAS ONLY Fuel Capacity (U. S. gal) Usable Fuel, Aviation Grade (min octane) 0-360-A4A or 0-360-A4M 180 2700 5. 125 4. 375 361.0 8. 5:1 285 76EM8S5-0-60 48 100/130 OIL Oil Capacity (qts) BAGGAGE Maximum Baggage (Ibs) Baggage Space (cubic ft) Baggage Door Size (in.) 200 24 20x22 DIMENSIONS Wing Span (ft) Wing Area (sq ft) Wing Loading (Ibs per sq ft) Length (ft) Height (ft) Power Loading (Ibs per hp) 32 170 14.4 24.0 7.8 13.6 LANDING GEAR Wheel Base (ft) Wheel Tread (ft) Tire Pressure (psi) Tire Size Nose Main Nose (4 ply rating) Main (4 ply rating) 6.7 10 24 24 6. 00 x 6 6. 00 x 6 1-2 GENERAL SPECIFICATIONS REVISED: MARCH 16, 1984 CHEROKEE ARCHER u-rojr B" n'tjr' ir »• ft- • --1 [^ r IN" mm i ru" GENERAL SPECIFICATIONS ISSUED: JULY 9, 1973 1-3 BLANK PAGE DESCRIPTION AIRPLANE AND SYSTEMS The Airplane................ Airframe .............. Engine and Propeller.......... Landing Gear........ Flight Controls.............. Fuel System............. Electrical System......... Vacuum System....... Instrument Panel...... Pitot-Static System.......... Heating and Ventilatuig System.....' Cabin Features........... Baggage Area................... Stall Warning............................. """"""" Finish................. Air Conditioning........... Piper External Power, .. 2-1 2-1 2-1 2-3 2-3 2-4 2-6 2-9 .. 2-9 .. 2-12 .. 2-12 .. 2-14 . 2-14 . 2-14 ... 2-14 . 2-15 2-16 2-i BLANK PAGE CHEROKEE ARCHER DESCRIPTION AIRPLANE AND SYSTEMS THE AIRPLANE The PA-28-180 Cherokee is a single-engine, low-wing monoplane of all metal construction. Its full 4-place seating, two hundred pound baggage capacity, 645 mile range and economical operation, coupled with the lively performance of a 180 horsepower engine, make this Cherokee a versatile airplane in the business and personal aviation fields'. 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 tough fiberglass. 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. The wing airfoil section is a laminai_flow type, NACA652-415 with the maximum thickness about 40% aft of the leading edge. This permits the main spar carry-through structure to be located under the rear seat, providing unobstructed cabin floor space ahead of the rear seat. ENGINE AND PROPELLER The Cherokee 180 is powered by a Lycoming 0-360-A4A or 0-360-A4M four cylinder, direct drive, horizontally opposed engine rated at 180 horsepower at 2700 rpm. It is furnished with a starter, a 60ampere, 14 volt altemator, a shielded ignition, vacuum pump drive, a fuel pump, and a dry, automotive type carburetor air filter. The exhaust system is of the cross-over type to reduce back pressure and improve performance. It is made entirely from stainless steel and is equipped with dual mufflers. A heater shroud around the mufflers is provided to supply heat for the cabin and windshield defrosting. The Sensenich 76EM8S5-0-60 fixed-pitch propeller is made from a one-piece alloy forging. ADtPLANE AND SYSTEMS REVISED: NOVEMBER 21, 1975 2-1 CHEROKEE ARCHER V \ \ ^ 0 V- \\ \ .\ \ /- / \/ Main Wheel Assembly 2-2 AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 CHEROKEE ARCHER LANDING GEAR The three landing gears use Cleveland 6. 00 x 6 wheels, the main gear wheels being provided with brake dmms and Cleveland single disc hydraulic brake assemblies. All three wheels use 6. 00 x 6, four-ply rating. Type HI 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. A spring device incorporated in the rudder pedal torque tube assembly aids in rudder centering and provides rudder trim. The nose gear steering mechanism also incorporates a bungee assembly to reduce steering effort and to dampen shocks and bumps during taxiing. A 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 4. 50 inches for the main gear. The standard brake system for this Cherokee consists of dual toe brakes attached to the rudder pedals 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. AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 2-3 CHEROKEE ARCHER -<- ^ ^^^' ?. '? ' ^i;^;','. '^/:'. ^"'' ^ » ^ "- ^ ^^'- '^f - ' ^©""' Console 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. 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 the 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 used as a step. The flaps have three extended positions, 10, 25 and 40 degrees. 2-4 AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 CHEROKEE ARCHER / ^^ \ 10 5 r 30 •^lv 'V." J> '• ./ I ^ -k \ \ \< -II . r^j 9i L // ^ r^ \ 1^ •\ ^ A .«-^ \ 6\ Throttle Quadrant and Console AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 2-5 CHEROKEE ARCHER V7' Fuel Selector 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. This allows easy removal for service or inspection. The 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 tank 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 container 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 sediment accumulation. To drain the lines from the tanks, the tank selector valve must be switched to each tank in turn, with the electric pump on, and the gascolator drain valve opened. (Refer to the 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 quadraat. 2-6 AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 FUEL QUANTITY GAUGES \tlIf/ \\tII/ CHEROKEE ARCHER 3 FUEL TANKSEUCTOR VALVE NAffl TANK FUEL STRWNER PRINER / ® MAIN TANK ENGINE RIB. PUNP ELECTRIC FUEL PUNP FUEL PRESSURE GAUGE MIXTURE THROTTLE 6€): CARBURETOR Fuel System Schematic AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 2.7 CHEROKEE ARCHER 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. The battery is mounted in a stainless steel box immediately aft 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. A 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. The alternator system offers many advantages over the generator system both in operation and maintenance. The main advantage is full electrical power output at lower engine RPM. This is a great improvement for radio and electrical equipment operation. Since the alternator output is available at all times, the battery will be charging for a greater percentage of use. This will make cold weather starting easier. Standard electrical accessories include a starter, electric fuel pump, stall warning indicator, cigar lighter, fuel gauge, ammeter, and annunciator panel*. The annunciator panel includes altemator 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 a full complement 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 proximity to ground, during takeoff and landing. The words "master switch" used hereafter in this manual indicate both sides of the switch: battery side "BAT" and altemator side "ALT" are to be depressed simultaneously to OFF or ON as directed. *Serial nos. 7505001 and up 2-8 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 these flight conditions. The amount of current shown on the ammeter will tell immediately if the altemator 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 ampere output breaker and reset if open. If neither circuit breaker is open, turn 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: MARCH 26, 1979 2-8a CHEROKEE ARCHER STARTER 8 ACCESSORIES ALTERNATOR FIELD > < STARTER SOLENOID STARTER SWITCH STftRTER r^'.,CIGAR LIGHTER CABIN LIGHT EXTERNAL POWER SOLENOID I EXTERNAL POWER RECEPTACLE I I L -_ _ -_ _ _ „ _ OPTJSN^.1-_ _ _J MASTER SOLENOID > . 1.1 I I r(L-__-_J -I- ALTERNATOR SOURCE-POWER RELAY ENERGIZING CIRCUIT AMMETER VOLTAGE REGULATOR OVER VOLTA6E PROTECTOR 1 MASTER SWITCH ALTERNATOR Altemator and Starter Schematic (Ser. nos. 7405001 through 7405290) 2-9 AIRPLANE AND SYSTEMS REVISED: JUNE 17, 1974 CHEROKEE ARCHER STARTER a ACCESSORIES V ALTERNATOR FIELD 5A (IN LINE) r>' STARTER SOLENOID ^ CIGAR I LIGHTER 1, -"^ r CABIN ; LISHT ^ EXTERNAL POWER RECEPTACLE ^ WARN . ALT ; LIGHT EXTEflNAL POWER SOLENOID I STARTER swrrcH '-' J-w'l MASTER '; SOLENOID ^ 5A (INLiNE) i y STARTER LAMP TEST •I'll 1 OPTIONAL ALTERNATOR SOURCE-POWER RELAY ENERGIZING CIRCUIT AMMETER VOLTAGE REGULATOR OVER VOLTAGE PROTECTOR MASTER ---/ SWITCH 1 ALTERNATOR Altemator and Starter Schematic (Ser. nos. 7505001 and up) AIRPLANE AND SYSTEMS ISSUED: JUNE 17, 1974 2-9a CHEROKEE ARCHER /'/ \ // \\ ^ •••'"', Circuit Breaker Panel 2-10 AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 CHEROKEE ARCHER VACUUM SYSTEM The vacuum system is designed 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 has remained constant over an extended period may indicate a dirty filter, dirty screens, possibly a sticking vacuum regulator or leak in system (a low vacuum indicator light 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 damage to the system components or eventual failure of the system. A vacuum regulator is provided in the system to protect the gyros. The valve is set so the normal vacuum reads 5. 0 ± . 1 inches of mercury, a setting which provides sufficient vacuum to operate all the gyros at their rated R.P.M. Higher settings will damage the gyros and with a low setting the gyros will be unreliable. The regulator is located behind the instrument panel and is accessible from below the instrument panel. mSTRUMENT PANEL The instrument panel 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. A natural separation of the flight group and power group is provided by the placement of the flight group in the upper instrument panel and the power group in the center and lower instrument panels. The radios and circuit breakers are on the right hand instrument panel. Extra circuits are provided for a complete line of optional radio equipment. An annunciator panel* is mounted in the upper instrument panel to warn the pilot of a possible malfunction in the altemator, oil pressure, or vacuum systems. *Serial DOS. 7505001 and up AmPLANE AND SYSTEMS REVISED: JUNE 17, 1974 2. 11 M K 11 5 6 7 8 41 9 10 12 13 14 15 IB 17 18 19 § I I "? ^ -' o; ccOo-o • » > ^ ..-"^':1:^. ^- .,. ¥••?-- ^ ^.a" ~ . ^ \1 ~<9 ce^ccoooo, ...,,. 't a 0' • 0 i;:^, WW, ^ t. OCKON^ -. ^^W^h, CUIUTtCONTDOLCTNTllt m i § H 2^ !i -3! ^1 ^ n»n -".•". •••W TW..^:--^ ni -y^ M 21 22 23 24 25 26 27 1. STALL WARNING LIGHT 2. CLOCK 3. TURN INDICATOR 4. AIRSPEED INDICATOR 5. DIRECTIONAL GYRO 6. ATTITUDE GYRO 7. VERTICAL SPEED INDICATOR 8. ALTIMETER 9. TRANSPONDER 10. MARKER BEACON 11. MAGNETIC COMPASS 12. OMNI & GLIDE SLOPE INDICATORS 13. AUDIO SELECTOR PANEL 14. UHFTRANSCEIVERS Z8 n w » "• I 29 30 31 i!El| h 32 33 34 35 '. '< M ' •? 36 37 15. ADF RECEIVER 16. DME RECEIVER 17. CIGAR LIGHTER 18. SUCTION GAUGE 19. HEAT & DEFROST CONTROL 20. MIKE JACK 21. PHONE JACK 22. AUTOPILOT 23. ENGINE INSTRUMENT.CLUSTER 24. OMNI COUPLER 25. NAV SWITCH 26. MAGNETO & STARTER SWITCH 27. PITCH CONTROL 28. CHECKLIST ^iS2i°°__1-^1 38 39 40 29. TACHOMETER 30. FUEL GAUGES 31. PRIMER 32. MICROPHONE 33. THROTTLE QUADRANT 34. FRICTION LOCK 35. CARBURETOR HEAT CONTROL 36. EGT INDICATOR 37. INSTRUMENT PANEL LIGHTS 38. CIRCUIT BREAKER PANEL 39. CIRCUIT BREAKER COVER 40. CLIMATE CONTROL 41. ANNUNCIATOR PANEL (SER. NOS. 7505001 AND UP) ^a B § p 0 >. •• 9.3. i® 0 ^M ^ 1ai 3 U1 @ ^ I M s 1. ALTIMETER 2. AIRSPEED INDICATOR 3. PITOT HEAT SWITCH 4. VERTICAL SPEED INDICATOR 5. PITOT HEAT g H I CHEROKEE ARCHER PFTOT-STATIC SYSTEM The system supplies both pitot and static pressure for the airspeed indicator, altimeter and vertical speed indicator (when installed). Pitot and static pressure are picked up by the pitot head on the bottom of the left wing. An optional heated pitot head, which alleviates problems with icing or heavy rain, is available. The switch for pitot heat is located on the switch panel above the throttle quadrant. To prevent bugs and water from entering the pitot and static pressure holes, when the airplane is parked, 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. HEATING AND VENTILATING SYSTEM Heat for the cabin interior and the defroster system is provided by 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 located on top of the heat ducts next to the console. Fresh air inlets are located in the leading edge of the wing at the intersection of the tapered and straight sections. A large adjustable outlet is located on the side of the cabin near the floor at each seat location; overhead air outlets are offered as optional equipment. Air is exhausted through an outlet under the rear seat. A cabin air blower, incorporated 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 "FAN" switch with 4 positions - "OFF, " "LOW, " "MED, " or "HIGH." CAUTION When cabin heat is operated, heat duct surface becomes hot. This could result in bums if arms or legs are placed too close to heat duct outlets or surface. 2. 14 AIRPLANE AND SYSTEMS REVISED: MARCH 26, 1979 ^^ I! H IIw@ l-i Vl ^ 102 M &: ? !TO I s< ^. r ^ 1 FRESH AIR INLET 2. DRAIN TUBE 3. FRESH AIR SLOWER 4. BULKHEAD ASSEMBLY 5. FRESH AIR DUCT 6. CABIN EXHAUST OUTLET 7. DEFROSTER OUTLET 8. BLOWER SWITCH PANEL 9. DEFROSTER CONTROL 10. NEATER CONTROL 11. CABIN HEAT DIVERSION CONTROL 12. FRESH AIR CONTROL e ? FRESH AIR CABIN HEAT 3^ / / 10 / (r^ 1'/-N " / / I.. —^' CHEROKEE ARCHER CABIN FEATURES Forjsase of entry and exit and pilot-passenger comfort, the front seats are adjustable fore and aft. The back of the right front seat contains two latches, an outboard latch which allows the seat to be moved forward or aft for ease of entry, and an inboard latch which allows the seat back to be tilted forward to allow easy entry to the rear seats. The rear seats are easily removed to provide room for bulky items. Some rear seat installations incorporate leg retainers with latching mechanisms which must be released before the rear seats can be removed. Releasing the retainers is easily accomplished by turning the latching mechanisms 90° with a coin or screwdriver. Armrests are also provided for the front seats. All 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. A single strap shoulder harness controlled by an inertia reel is standard equipment for the front seats, and 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. A check of the inertia reel mechanism is made by pulling sharply on the 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. BAGGAGE AREA A 24 cubic foot baggage area, located behind the rear seats, is accessible either from the cabin or through a large 20 x 22 inch 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. (See Weight and Balance Section.) STALL WARNING An approaching stall is indicated by a stall warning light located on the left side of the instrument panel. The red light illuminates automatically between five and ten miles per hour above stall speed. FINISH All exterior surfaces are primed with etching primer and finished with a durable acrylic lacquer in a variety of tasteful colors to suit individual owners. 2-16 AIRPLANE AND SYSTEMS REVISED: MARCH 16, 1984 CHEROKEE ARCHER 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 "ON" and retracts to a flush position when the system is "OFF." The compressor is mounted on the forward right underside of the engine. It has an electric clutch which automatically engages or disengages the compressor to the belt drive system of the compressor. An 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 control clockwise for increased cooling, counterclockwise for decreased cooling. Located inboard of the temperature control is the fan speed switch and the air conditioning "ON-OFF" 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 in 5 minutes, turn the system "OFF" until the fault is corrected. The "FAN" switch allows operation of the fan with the air conditioner turned "OFF" 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 OPEN" indicator light is located to the left of the radio stack in front of the pilot. The light illuminates whenever the condenser door is open and remains on until the door is closed. A circuit breaker located on the circuit breaker panel protects the air conditioning electrical system. *0ptional equipment AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973 2-17 CHEROKEE ARCHER 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 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. 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. *0ptional equipment 2. 18 AIRPLANE AND SYSTEMS ISSUED: JULY 9, 1973