PILOT'S OPERATING MANUAL

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont) r Revision Revised Description Date Pages Rev. 11 (cont) 7-4 Added to text info. 9-i Added Warning. 10-1 Added to text info. 10-8, 10-9 Added to text info. 10-11 Revised para. 10-12 Revised para. 10-13 Deleted text info. Rev. 12 - 761 557 iv-c Added Rev. 12 to.761557 Log of Revisions. June 16, 1990 (PR900616) 10-8 Revised Oil Requirements. Moved Fuel System to page 10-Sa. 10-Sa Added page. Revised and moved Fuel System from page 10-8. 10-Sb Added page. 10-9 Revised Fuel Grade Comparison Chart. 10-11 Revised Handling and Seivicing (Facts You Should Know). 10-13 Revised Required Seivice and Inspection Periods. iv-c l_ · TABLE Of 'CONTENTS GENERAL SPECIFICATIONS DESCRIPTION - AIRPLANE AND SYSTEMS AIRPLANE FLIGHT MANUAL F.A.A. APPROVED EMERGENCY PROCEDURES F.A.A. APPROVED EMERGENCY PROCEDURES WBGHT AND BALANCE LOADING INSTRUCTIONS OPERATING INSTRUCTIONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SERVICING V I • ) '· • _) .I GENERAL SPECIFICATIONS 1- 0 ( . ( .,) GENERAL SPECIFICATIONS Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 Weigh ts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1- 2 Power Plant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 Fuel and Oil .... ; . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 Baggage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . 1-2 Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I -2 Three-View . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 1-i ·1 I I,, 0 ( L- \ f ' \ • jL { Clll<:ROKl•:E PATIIFINl>ER GENERAL SPECIF'ICATIONS PERFORMANCE Published figures are for standard airplanes flown at gross weight under standard conditions at sea level, unless otherwise stated. Performance for a specific airplane may vary from published figures depending upon the equipment insta1led, the condition of engine airplane and equipment, atmospheric corrdition and pi loting technique. Each performance figure below is subject to the same conditions as on the corresponding perfonnance chart from which it is taken in the Performance Charts Section. Takeoff Ground Run, no flaps sea level (ft) Takeoff Ground Run, 25 ° flaps, sea level (ft) Takeoff Distance Over 50-ft Obstacle, no 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, 6500 ft, 75% power (TAS) (mph) Service Ceiling ( ft) Absolute Ceiling (ft) Cruise Speed at best power mixture (mph) 65% power, 9,000 ft 5 5% power, I 1,800 ft Range at best power mixture (mi)** 75% power, 6,500 ft 65% power, 9,000 ft 55% power, 11,800 ft Cruise Speed at best economy mixture (mph) 75% power, 6,500 ft 65% power, 9,000 ft 55% power, 11,800 ft Range at best economy mixture (mi)** 75% power, 6,500 ft 65% power, 9,000 ft 5 5% power, 1 1,800 ft Stalling Speed, flaps down (CAS) (mph) Stalling Speed, flaps up (CAS) (mph) Landing Roll, flaps down, sea level (ft) Landing Roll Over 50-ft Obstacle, sea level (ft) 850 800 1410 1260 100 800 90 161* 153* 13,550 15,500 146 138 805 925 990 145 138 130 915 1040 1110 65 73 1040 1740 * All speeds stated are with optional wheel fairings installed. Subtract 3 mph if wheel fairings are not installed. **No reserve. GENERAL SPECIFICATIONS ISSUED: JULY 10, 1973 1-1 CHEROKEE PATHFINDER WEIGHTS Gross Weight (lbs) Standard Empty Weight (lbs) Maximum Useful Load (lbs) POWER PLANT Engine - Lycoming Rated Horsepower Rated Speed (rpm) Bore (inches) Stroke (inches) Displacement (cubic inches) Compression Ratio _ Dry Weight (pounds) Propeller - Hartzell FUEL - I AVGAS ONLY OIL Usable Fuel Capacity (main tank) (U.S. gal) Usable Fuel Capacity (auxiliary tanks) (U.S. gal) Fuel, Aviation Grade Minimum Octane Specified Octane Alternate Fuels Oil Capacity (U.S. qts) BAGGAGE Maximum Baggage (lbs) Baggage Space (cubic ft) Baggage Door Size (in.) DIMENSIONS Wing Span (ft) Wing Area (sq ft) Wing Loa:ding (lbs per sq ft) Length (ft) Height (ft) Power Loading (lbs per hp) LANDING GEAR 1-2 Wheel Base (ft) Whcd Tread (fl) ·1 ire Pressure (lhs) Nose Main 3000 1565 1435 O-540-B4B5 235 2575 5.125 4.375 541.5 7.2:l 395 HC-C2YK-I( )F/F8468-4 48 34 80/87 80/87 Refer to Fuel Requirements, Section 10 - Page 10-8 12 200 24 20 X 22 32.0 170 17.6 24.l 7.5 12.8 6.6 l0.0 28-JO J5-40 GENl(RAI, SPEC'.IFICATIONS IH'.VISl•:I>: MAIH'II 20. 1984 ( CHEROKEE PATHFINDER - - ---12 ' 10.&"·------t 3 ,. 6 .. 0 0 0 - --------- --32' 1.80"----------------1 GENERAL SPECIFICATION ISSUED: JULY 10, 1973 1-3 I,. { DESCRIPTION AIRPLANE AND SYSTEMS ( .. ( , I (.J ,. DESCRIPTION AIRPLANE AND SYSTEMS ------~T=~=A = k ~ l=~=e~ ... .... . . ........ . .... . ............. .. .... .. ~1 Airframe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Engine and Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 L~ding Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 Pitot-Static System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Heating and Ventilating System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Vacuum System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Cabin Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 Baggage Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 7 Stall Warning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 7 Finish . . . . . . . . . . . . . . . . . . . .., . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 Piper External Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 • 2-i I • THE AIRPLANE DESCRIPTION AIRPLANE AND SYSTEMS CHEROKEE PATHFINDER The PA-28-235 Cherokee is a single-engine, low-wing monoplane of all metal construction. The airplane will comfortably seat four adult passengers. The Cherokee Pathfinder is designed and manufactured as a versatile airplane in the personal and business aviation fields. AIRFRAME Fxcept for the tubular steel engine mount. steel gear struts, and some miscellaneous steel parts. all metal structures in the airplane are of aluminum alloy construction. The nose cowl, the wing tip tanks, and various other nonstructural components are fiberglass. The wings arc a ttachcd to each side of the fuselage by the 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 arc also fore and aft attachments at the rear spar and at an auxiliary front spar. The wing airfoil section is a laminar flow type. N AC A 6 52 -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 sea L providing unobstructed cabin floor space ahead of the rear scat. ENGINE AND PROPELLER The Lycoming 0-540-134135 engine installed in the Cherokee PA-28-235 is rated at 235 horsepower at 2575 rpm. This engine has a compression ratio of 7.2 to 1 and requires 80/87 minimum octane aviation fuel. TI1e engine is equipped with a geared starter, a 60 ampere alternator. dual magnetos, shielded ignition system, vacuum pump drive, a diaphragm-type fuel pump and a float carburetor . Exhaust gases are carried through a heavy gauge stainless steel system which incorporates two heater shrouds, one for cabin heat and the other for carburetor deicing. The propeller used on the PA-28-235 is a Hartzell HC-C2YK-I ( )F /F8468-4 constant speed 11ropcllcr. TI1e Hartzell propeller is 80 inches in diameter. and is controlled by a Hartzell F-4-> !!0vernor mounted on a pad on the forward end of the crankcase.This governor supplies oil to the propeller through the engine shaft. The governor is controlled by a cable from the L'OCkpit AIRPLANE AND SYSTEMS REVISED: DECEMBER 2. 1975 2-1 CHEROKEEPA1HFINDER The two-piece cowling on the Cherokee is designed to cool the engine in all normal flight conctitions, including protracted climb, without the use of cowl flaps or cooling flanges. The throttle quadrant, located in the lower center instrument panel, contains the throttle, mixture control, and the propeller governor control. A friction lock on the right side of the quadrant prevents creeping of the controls. In addition, the mixture control has a lock* to prevent activation of the mixture control instead of the pitch control. To the right of the quadrant is the carburetor heat control. Maximum carburetor heat is provided with the control in the "ON" position. Air passes through a high-efficiency dry-type filter when the carburetor heat is in the "OFF" position. LANDING GEAR The landing gears use Oeveland 6.00 x 6 wheels, the main wheels being provided with brake drums and single disc hydraulic brakes. The nose wheel carries a 6.00 x 6 four ply rating tire with tubes, while the main gear uses 6.00 x 6 six ply rating tires. By use of the rudder pedals and brakee the note 1ear is steerable throuah a 30 degree arc each side of neutral. A spring device is incorporated in the rudder pedal torque tube assembly to provide rudder trim. A bungee in the nose gear steerina mechanism reduces steering effort and dampens bumps and shocks during taxiing. A shimmy dampener is also included in the nose gear. The oleo struts are of th e air-o.il type, with a normal extension of 3-1 /4 inches fo r the nose gear and 4- l /2 inches for the main gear under normal static load (empty weight of airplane plus full fuel and oil). The brakes are actuated by a l1and lever and master cylinder, which is located below and near the center of the instrument panel. The toe brakes and the lever have their own brake cylinders, but they share a common reservoir. The parking brake is incorporated in the lever brake and is operated by pulling back on the lev er and depressingthe knob attached to the top of the handle . To release the parking brake, pull back on the brake lever to disengage the catch mechanism; then allow the handle to swing forward . *Serial nos . 7510001 and up AIRPLANE AND SYSTEMS - -- - . - -- ----- - - - -·-- -= -- ·- REVISED: JUNE 12, 1974 , I AIRPLANE AND SYSTEMS ISSUED: JULY 10, 1973 CHEROKEE PATHFINDER Main Wheel Assembly 2-3 CHEROKEEPAfflFINDER ' 2-4 :~\ I i ,'" 7.~~ \,~~.,.,, Throttle Quadrant and Console AIRPLANE AND SYSTEMS _ _ REYISED: JJJLY 11, 19_75 _ CHEROKEE PATH FINDER Console FLIGHT CONTROLS Dual controls are provided as standard equipment, with a cable system used between the controls and the surfaces. The horizontal tail is of the all-movable slab type, with an anti-servo tab which also acts as a longitudinal trim tab, actuated by a control mounted on the control tunnel between the two 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 eliminate adverse yaw in turning maneuvers and to reduce the amount of coordination required in normal turns. 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. AIRPLANE AND SYSTEMS ISSUED: JULY 10, 1973 2-5 CHEROKEE PATHFINDER FUEL SYSTEM Standard fuel capacity of the Cherokee 235 is 84 gallons, of which 82 gallons is usable. The two main inboard tanks, which hold 25 gallons each, 24 gallons usable each, are attached to the wing structure with screws and nut plates and may be easily removed for service or inspection. The resin-impregnated fiberglass tip tanks have a capacity of 17 gallons each, all of which is usable. The fuel selector control is located below the center of the instrument panel on the sloping face of the control tunnel. It has five positions corresponding to each of the four tanks, plus an "OFF" position. When using less than the standard 84 gallon capacity of the tanks, fuel should be distributed equally between each side, filling the tip tanks first. The fuel system should be drained daily prior to first flight and after refueling to avoid the accumulation of water, sediment and to check for proper fuel (a special bottle is furnished for this operation). Each fuel tank is equipped with an individual quick drain located at the lower inboard rear corner of the tank. The fuel strainer and a system quick drain valve are located in the fuselage at the lowest point of the fuel system. It is important that the fuel system be drained in the following manner: I. Drain each tank through its individual quick drain located at the lower inboard rear corner of the tank, making sure that enough fuel has been drained to ensure that all water and sediment is removed. 2. Place a container under the fuel sump drain outlet, which is located under the fuselage. 3. Drain the fuel strainer by pressing down on the lever located on the right-hand side of the cabin below the forward edge or the rear scat. The fuel selector must be positioned in the following sequence: off position, left tip, left main, right main, and right tip while draining the strainer to ensure that the fuel lines between each tank outlet and fuel strainer are drained as well as the strainer. When the fuel tanks are full, it will take approximately 11 seconds to drain all the fuel in one of the lines between a tip tank and the fuel strainer and approximately six seconds to drain all the fuel in one of the lines from a main tank to the fuel strainer. When the fuel tanks are less than full, it will take a few seconds longer. 4. Examine the contents of the container placed under the quick drain and the fuel sump drain outlet for water, sediment and proper ruel. Then dispose of the contents. AIRPLANE ANI> SVSTEMS 2-6 IH:VISEI>: MAIH'II 20, 1984 CHEROKEE PATHFINDER -..., ---- ....- - Fuel Drain Lever CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. After using the underseat quick drain, it should be checked from outside to make sure it has closed completely and is not leaking. Fuel quantity gauges for each of the four tanks are located in the engine gauge cluster on the left side of the instrument panel. A fuel pressure indicator is also incorporated in the engine gauge cluster. An electric fuel pump is provided for use in case of failure of the engine driven pump. The electric pump operates from a single switch and independent circuit protector, and should be ON for all takeoffs and landings. An optional engine priming system is available to facilitate starting. The primer pump is located to the immediate left of the throttle quadrant. AIRPLANE AND SYSTEMS ISSUED: JULY 10, 1973 2-7 CHEROKEEPAIBFINDER _, c:, I!:z <111 11~ c:, E[] u "" ""z l,1 c:, C ...u ... .., :a: ' _, c ..,.,, a _, !i: ..,::::, ... I .... ii: ~ Fuel System Schematic 2-8 ;:.:1 i:! e ..,_,.., AIRPLANE AND SYSTEMS - -- -- ISSUED~ JlJb¥- -10, -197-3-- ( CHEROKEEPAIBFINDER ELECTRICAL SYSTEM The electrical system includes a 14-volt 60 amp alternator, voltage regulator, overvoltage relay, and master switch relay. The 12-volt 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 instruITient 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. Standard electrical accessories, include starter, electric fuel pump, stall warning indicator, cigar lighter, and ammeter. Optional electrical acce~ories includes navigation, anti-collision, landing, instrument and cabin dome lighting. The words "master switch" used hereafter in this manual indicate both sides of the switch; battery side "BAT" and alternator side "ALT" are to be depressed simultaneously to OFF or ON as directed. Circuit provisions are made to handle a full complement of communications and navigational equipment. The alternator system offers many advantages over the generator system. The main advantage is full electrical power output at much lower engine RPM. 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 the 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 whether the alternator system is operating normally, as the amount of current shown should equal the total amount of amperes being 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 I 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 pe required, contact the local Piper Dealer. AIRPLANE AND SYSTEMS REVISED: NOVEMBER 9, 1973 2-9 CHEROKEE PATHFINDER ALTERNATOFI FIELD !!AMP ) - \ \ - \ \ \ \ 'I \ \ \ \ \ I \ ~------ -- - - ----- , EXTERNAL POWER RECEPTACLE EXTERNAL POWER II CONTACTOR I I L ______ _ OPTIONAL ___ _ j 2-10 \ \ VOLTAGE REGULATOR \ I \ I \ +, : \ - \ ALTERNATOR OUTPUT C/B A - I .--1-----M')-Y \ \ \ \ \ \ \ \ \ \ ~MASTER \,;lSWITCH STARTER & ACCESSORIES STARTER SWITCH CIGAR LIGHTER i t: STARTER r - - - - - - - - - -- , ALTERNATOR SOURCE : POWER RELAY L _ _ _ __ _____ ~ENERGIZING CIRCUIT Alternator - Starter Schematic AIRPLANE AND SYSTEMS _ISSUED: JULY _l0,1973_ CHEROKEE PATHFINDER PITOT-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 heatecl 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 lower right side of the instrument panel. 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. This blower is operated by a "FAN" switch with 4 positions - "OFF," "LOW," "MED," or "HIGH." AIRPLANE AND SYSTEMS ISSUED: JULY 10, 1973 2-11 CHEROKEEPAIBFINDER 0 \J\\ - --i \ I~ \\, \ \ - ,' , • '-... ... - I ...._ ~I I- <( w I z a: <( I (/) aJ w <( a: u u. ....._ I I o• .-fNM'Cl'M'>I.Qr--.oocno..-tN 2-12 I Heat, Defrost and Ventilating System I I \ I ) I AIRPLANE AND SYSTEMS ISSUED:- JUtY-l0; 1973-- ( \ AIRPLANE AND SYSTEMS REVISED: JULY 11, 1975 • ~~~ ~-~'~ '\~ ~'\ ~ -~ ~~. ~ -~, ~""'5~~ ~~ ~} ~,', ~ ~~ ~ ~ ,- Q-5 ~ ~'"" '.,' -\. ~ - ;, '~ ~'• ~~~ ~~~ ~ ~'~ . ~~ ,. CHEROKEE PATHFINDER · -.... a: 0 0 0 ui > z .J <tz II. 0 a: j UJ UJ :11::0 It 0 ~:i: m>- 1- .J - a: :::> It u UJ ~z uo ·\ :, ..-. ·, • \ \.~)\• ,\ \, ~~ '\'Si~ -~.::t f l-,':·.i:'_. ·-~..;: ... Circuit Breaker Panel 2-13 CHEROKEE PATHFINDER 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 RPM. Higher settings will damage the gyros and with a low setting the gyros will be unreliable. The regulator is located behind the instrument panel. INSTRUMENT PANEL The instrument panel of the Cherokee is designed to accommodate the customary advanced flight instruments and the normally required power plant instruments. TI1e 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, and 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 alternator, oil pressure, or vacuum systems. *Serial nos. 7510001 and up 2-14 AIRPLANE AND SYSTEMS .. REYISED: JUNE 12, 1974 . ) ·) ~==:$~ ~s:t::I z •• t!1 ~> ?z~o - r.ll :-'~ -~ \C) ~!r.ll NI - VI - ::s ~ ,2 9Cl) ::s.... '"'d la) ~ - I 6 7 ~ """""" EJ--: . - .. ~ 21 22 23 24 25 26 27 28 29 l. STALL WARNING LIGHT 2. ADF INDICATOR 3 . CLOCK 4. TURN & BANK 5 . AIRSPEED 6. DIRECTIONAL GYRO 7. GYRO HORIZON 8. VERTICAL SPEED INDICATOR 9. ALTIMETER 10. TRANSPONDER 11. MARKER BEACON 12. COMPASS 13. UHF INDICATOR 14. AUDIO SELECTOR PANEL 15. UHF TRANSCEIVERS 16. ACF RADIO ) 12 11 42 14 15 16 17 44 19 18 20 30 31 32 33 34 35 43 36 37 38 39 40 41 17. DME RADIO 33. MICROPHONE 18. CIGAR LIGHTER 34. THROTTLE QUADRANT n19. SUCTION GAUGE 35. FRICTION LOCK = 20. HEAT & DEFROSTER CONTROL 36. CARBURETOR HEAT LOCK t!1 21. MIKEJACK 37. EGT INDICATOR "' 22. PHONE JACK 38. INSTRUMENT PANEL LIGHTS 0 23. AUTOPILOT 39. CIRCUIT BREAKER PANEL ~24. ENGINE INSTRUMENT CLUSTER 40. CIRCUIT BREAKER COVER (ON EARLY 25. OMNI COUPLER MODELS ONLY) 26. NAV SELECTOR SWITCH 41. OPTIONAL FRESH AIR '"d 27. PITCH TRIM, ON/OFF BLOWER CONTROL ~28. MAGNETO& STARTER SWITCH 42. ANNUNCIATOR PANEL (SER. NOS. 29. FUEL GAUGES 7510001 AND UP) 30. MANIFOLD PRESSURE GAUGE 43. MIXTURE CONTROL LOCK (SER. ; 31. TACHOMETER NOS. 7510001 AND UP) 32. PRIMER 44. ENGINE HOUR METER i "' ., CHEROKEE PATHFINDER 2-16 \ '\ \i \~ ~-- ~I I/ I ~ Pitot - Static System AIRPLANE AND SYSTEMS ___ ISSUED : JULY 10,J 973 (........ - CHEROKEEPAIBFTNOER CABIN FEATURES For ease of entry and exit and pilot-passenger comfort, the front seats are adjustable fore and aft. All seats recline and are available with optional headrests. Armrests are also provided for the front seats which can also be equipped with optional vertical adjustment. The rear seats are adjustable one inch fore and aft by raising the rear of the seat and placing pins in alternate sockets. 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. 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 indicator which is activated between five and ten miles per hour above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall. Stall speeds are shown on graphs in the Performance Charts Section. The stall warning indicator is a red warning light on the left side of the instrument panel on earlier models and a continuous sounding horn located behind the instrument panel on later models. The stall warning indicator 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 "ON," lifting the detector and checking to determine if the indicator is actuated. FINISH All exterior surfaces arc primed with etching primer and finished with a durable acrylic lac4ucr in 11 variety of tastcl'ul colors to suit individual owners. AIRPLANE AND SYSTEMS REVISED: MARCH 20, 1984 2-17 CHEROKEE PATHFINDER 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 wirtg. 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. *Optional equipment 2-18 AIRPLANE AND SYSTEMS IS SUED :--Jl:JL--v---10,19"1''¾- 3 - - AIRPLANE FLIGHT MANUAL F.A.A. APPROVED AIRPLANE FLIGHT MANUAL FOR CHEROKEE PATHFINDER NOTE TIDS MANUAL MUST BE KEPT IN mE AIRPLANE AT ALL TIMES MANUFACTURER'S MODEL PA-28-235 MANUFACTURER'S SERIAL 28- 7410049 REGISTRATION - N;oso1 FAAAPPROVEDBY: $~~ hBARNHOUSE PIPER AIRCRAFT CORPORATION D. 0. A. No. S0-1 VERO BEACH, FLORIDA DATE OF APPROVAL: MAY 14, 1973 APPROVAL BASIS: CAR 3 REPORT: VB-559 MODEL: PA-28-235 l AIRPLANE FLIGHT MANUAL Log of Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-iii Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5 Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3- 7 Supplements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9 ... , •..j ,._ ( . CHEROKEE PATHFINDER TABLE OF CONTENTS Log of Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-iii SECTION I Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 A. Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 B. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 C. Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 D. Power Instrument . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 E. Airspeed Limitations and Instrument Markings (Calibrated Airspeed) . . . 3-2 F. Maximum Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2 G. C. G. Range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2 H. Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2 I. Placards . . . . . . . . . . . . . . . . . . . . , . . . . . . . . . . . . . . . . . 3-3 SECTION II Procedures . . . . . . . . . . . . . . . . . . . . . . . A. System Operations . . . . . . . . . . . . . B. Fuel System Preflight Procedure .. . . . SECTION ill Performance . . . . . . . . . . . . . . . . . . . . A. Stalls . . . . . . . . . . . . . . . . . . . SECTION IV 3-5 3-5 3-5 Optional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9 A. Electric Pitch Trim Installation ...... ..... ... ... , . . . . . . . 3-11 B. AutoFlite II Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12 C. Installation of Piper AutoControl III and/or AutoControl IIIB . . . . . . . 3-15 FAA APPROVED MAY 14, 1973 REVISED: JULY 11, 1975 REPORT: VB-559 PAGE 3-i MODEL: PA-28-235 CHEROKEE PATHFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-559 PAGE 3-ii ----·- ------M8DEL:-PA-- 28-235 -- FAA APPROVED MAY 14, 1973 ( .I CHEROKEE PATHFINDER AIRPLANE FLIGHT MANUAL LOG OF REVISIONS FAA Approved Revision Revised Pages Description and Revision Date 1 Title Added PAC Approval Form. t/H~,_,(_ (NOTE: AIRCRAFT DELIVERED WITH MANUALS PRIOR TO THIS REVISION D. H. Trompler DO NOT REQUIRE THIS REVISION.) June 3, 1974 2 3-i Added Item D. (Installation of Piper Auto- Control 111B) to Supplements. Ju~ l~.3-9 Added Item D. (Installation of Piper Auto- Control 111B). 3-15, 3-16, Added pages (AutoControl 11IB Supplement). D. H. Trompler 3-17, 3-18 June 12, 1974 3 3-9 Changed Section IV title (from Supplements) to Optional Equipment); revised NOTE; deleted item A. (AutoControl Ill); revised existing item letters. 3~1 1 Deleted item A. (AutoCon trol III). 3-12 Revised item letter (B to A); deleted with Pitch Trim Swith from title. 3-13 Revised item letter (C to B). 3-15 Revised item letter (D to C); added Auto (J CV\ df Vcw.v Control III to item title. 3-18 Removed IIIB designation from items c. l. and Ward Evans c.2. July 11, 1975 4 3-18 Revised item c. (1). (J J rQl'I c:;v~ Ward Evans Dec. 2, 1975 5 3-1 Revised item b. Fuel. WQ/\~~ Ward Evans April 23, 1976 6 Title Added serial no . applicability. (NOTE: AIRCRAFT DELIVERED WITH C~!i-..--..--- MANUALS PRIOR TO THIS REVISION Ward Evans DO NOT REQUIRE THIS REVISION.) June 13, 1980 FAA APPROVED MAY 14, 1973 REVISED: JUNE 13, 1980 REPORT: VB-559 PAGE 3-iii MODEL: PA-28-235 CHEROKEE PATHFINDER AIRPLANE FLIGHT MANUAL LOG OF REVISIONS (cont) FAA Approved Revision Revised Pages Description and Revision Date 7 3-1 Added to item B. 3-5 Revised procedure . - REPORT: VB-559 PAGE 3-iv MGDEL! -PA-28-2-35 - -- - (Jo,J.~ Ward Evans March 20, 1984 FAA APPROVED MAY 14, 1973 REVISED: MARCIi 20, 1984 I ( ·' REVISIONS TI1e information compiled in the Pilot's Operating Manual will be kept current by revisions distributed to the airplane owners. Revision material will consist of information necessary to update the text of the present manual and/or add information to cover added airplane equipment. I. Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the manual 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. IL Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the left hand margin of the page, opposite revised, added or deleted material. A line opposite the page number or section title and printing date, will indicate that the text or illustration was unchanged but material was relocated to a different page or 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 a page will not be identified by symbols. iii PILOT'S OPERA TING MANUAL LOG OF REVISIONS Current Revisions to the PA-28-235 Cherokee Pathfinder Pilot's Operating Manual, 761 557, issued July 10, 1973 Revision Revised Description DatePages Rev. 1 - 761 557 2-9 Revised Overvoltage Relay Reset Time. Nov. 9, 1973 (PR 731109) 4-7 Revised Alternator Failure Item 3. W/B Added Rev. 1 to Report: VB-548. 7-i Added Airspeed Data 7-8 Added Airspeed Data; Relocated E.L.T. 7-9 Added E.L.T. 7-10 Added Page. 8-1 Revised Item 6. iv SECTION I LIMITATIONS CHEROKEE PATHFINDER The following limitations must be observed in the operation of this airplane: A. ENGINE Lycoming O-540-B4B5 ENGINE LIMITS For all operations 2575 RPM, 235 HP B. FUEL (AVGAS ONLY) 80/87 minimum octane aviation fuel C. PROPELLER Hartzell HC-C2YK-1( )F/F8468A-4, pitch: high 27 degrees± 2 degrees, low 13.5 degrees ± .2 degrees at 30" station, maximum diameter 80 inches, minimum diameter 80 inches. D. POWERINSTRUMENTS OIL TEMPERATURE Green Arc (Normal Opera ting Range) Red Line (Maximum) OIL PRESSURE Green Arc (Normal Operating Range) Yellow Arc (Caution Range) Red Line (Minimum) Red Line (Maximum) FUEL PRESSURE Green Arc (Normal Operating Range) Red Line (Minimum) Red Line (Maximum) TACHOMETER Green Arc (Normal Operating Range) Red Line (Maximum Continuous Power) FAA APPROVED MAY 14, 1973 REVISED: MARCH 20, 1984 75°F to 245°F 245°F 60 PSI to 90 PSI 25 PSI to 60 PSI 25 PSI 90PSI .5 PSI to 8 PSI .5 PSI 8 PSI 500 to 2575 RPM 2575 RPM REPORT: VB-559 PAGE 3-1 MODEL: PA-28-235 CHEROKEE PATHFINDER E. AIRSPEED LIMITATIONS AND AIRSPEED INSTRUMENT MARKINGS (Calibrated Airspeed) NEVER EXCEED MAXIMUM STRUCTURAL CRUISE MANEUVERING FLAPS EXTENDED MAXIMUM POSITIVE LOAD FACTOR MAXIMUM NEGATIVE LOAD FACTOR AIRSPEED INSTRUMENT MARKINGS Red Radial Line (Never Exceed) Yellow Arc (Caution Range) (Smooth Air Only) Green Arc (Normal Operating Range) White Arc (Flaps Down Range) F. MAXIMUMWEIGHT G. C. G. RANGE 197 MPH 156 MPH 138 MPH 115 MPH 3.8 No inverted maneuvers approved 197 MPH (171 KTS) 156 MPH to 197 MPH (136 KTS to 171 KTS) 73 MPH to 156 MPH (62 KTS to 136 KTS) 65 MPH to 115 MPH (57 KTS to 100 KTS) 3000 LBS The datum used is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. Weight (Pounds) 3000 2500 1900 Forward Limit (In. Aft of Datum) 88.0 82.0 79.0 Straight line variation between points given. NOTE Rearward Limit (In. Aft of Datum) 91.5 91.5 91.5 It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded . See Weight and Balance Section for proper loading instructions. H. MANEUVERS No acrobatic maneuvers, including spins, approved. REPORT: VB-559 PAGE 3-2 MODEL:-PA-28-235 FAA APPROVED MAY 14, 1973 CIIEROKEEPATHFINDER I. PLACARDS In full view of the pilot: 1 "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED." "t Adjacent to upper door latch: "ENGAGE LATCH BEFORE FLIGHT." J On the inside of the baggage compartment door: "MAXIMUM BAGGAGE 200 LBS" 1../ On the instrument panel in full view of the pilot: "ROUGH AIR OR MANEUVERING SPEED 138 MPH." S On the instrument panel in full view of the pilot when the AutoFlite II is installed : "TURN AUTOFLITE ON. ADJUST TRIM KNOB FOR MINIMUM HEADING CHANGE. FOR HEADING CHANGE, PRESS DISENGAGE SWITCH ON CONTROL WHEEL, CHANGE HEADING, RELEASE SWITCH. ROTATE TURN KNOB FOR TURN COMMANDS. PUSH TURN KNOB IN TO ENGAGE TRACKER. PUSH TRIM KNOB IN FOR HI SENSITIVITY. LIMITATIONS AUTOFLITE OFF FOR TAKEOFF AND LANDING." ' On the instrument panel in full view of the pilot when the supplementary white strobe lights are installed: "WARNING -TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT, OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE." FAAAPPROVEDMAY,14, 1973 REPORT: VB-559 PAGE 3-3 • MODEL: PA-28-235 ' . CHEROKEE PATHFINDER THIS Pj\GE INTENTIONALLY LEFT BLANK REPORT: VB-559 PAGE 3-4 MODEL: PA-28~235 FAA APPROVED MAY 14, 1973 SECTION II PROCEDURES CHEROKEE PATHFINDER 1. The stall warning system is inoperative with the master switch off. 2. Electric fuel pump must be on for both landing and takeoff. 3. Except as noted above, all operating procedures for this airplane are normal. 4. Fuel System Preflight Procedure : The fuel system should be drained daily prior to first flight and after refueling to avoid the accumulation of water. sediment and to check for proper fuel. (a special bottle is furnished for this operation.) Each fuel tank is equipped with an individual quick drain located at the lower inboard rear corner of the tank. The fuel strainer and a system quick drain valve arc located in the fuselage at the lowest point of the fuel system. It is important that the fuel system be drained in the following manner: a. Drain each tank through its individual quick drain located at the lower inboard rear corner of the tank, making sure that enough fuel has been drained to insure that all water and sediment is removed. b. Place a container under the fuel sump drain outlet, which is located under the fuselage. c. Drain the fuel strainer by pressing down on the lever located on the right hand side of the cabin below the forward edge of the rear seat. The fuel selector must be positioned in the following sequence: off position, left tip, left main, right main, and right tip while draining the strainer to insure that the fuel lines between each tank outlet and fuel strainer are drained as well as the strainer. When the fuel tanks are full, it will take approximately 11 seconds to drain all the fuel in one of the lines between a tip tank and the fuel strainer and approximately six seconds to drain all the fuel in one of the lines from a main tank to the fuel strainer. When the fuel tanks are less than full, it will take a few seconds longer. d. Examine the contents of the container placed under the quick drain and the fuel sump drain outlet for water, sediment and proper fuel. Then dispose of the contents. CAUTION When draining any amount of fuel, care should be taken to insure that no fire hazard exists before starting engine. After using the under-seat quick drain, it should be checked from outside to make sure it has closed completely and is not leaking. FAA APPROVED MAY 14, 1973 REVISED: MARCH 20, 1984 REPORT: VB-559 PAGE 3-5 MODEL: PA-28-235 CHEROKEE PATHFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-559 PAGE 3-6 MODEL: PA.:.28~235 FAA APPROVED MAY 14, 1973 ). SECTION Ill PERFORMANCE All performance is given for a weight of 3000 pounds. CHEROKEE PATHFINDERI Loss of altitude during stalls can be as great as 350 feet, depending on configuration and power. Stalling speed, in mph vs. angle of bank (Calibrated Airspeed): Angle of Bank Flaps Up Flaps Down FAA APPROVED MAY 14, 1973 00 73 65 20° 75 40° 83 50° 91 60° 103 REPORT: VB-559 PAGE 3-7 MODEL: PA-28-235 .I l CHEROKEE PATHFINDER THIS PAGE IN,TENTIONALLY LEFT BLANK REPORT: VB-559 PAGE 3-8 MODEL: PA-28-235 FAA APPROVED MAY 14, 1973 SECTION IV OPTIONAL EQUIPMENT NOTE CHEROKEE PATHFINDER THE INFORMATION CONTAINED IN THIS SECTION APPLIES WHF;N THE RELATED EQUIPMENT IS INSTALLED IN THE AIRCRAFT. A. Electric Pitch Trim Installation B. AutoFlite II Installation C. Installation of Piper AutoControl III and/or AutoControl IIIB FAA APPROVED MAY 14, 1973 REVISED: JULY 11, 1975 REPORT: VB-559 PAGE 3~9 MODEL: PA-28-235 CHEROKEE PATHFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: vu ..559 PAGE 3-10 MODEL: PA-28-235 - • ' FAA APPROVED MAY 14, 1973 ( CHEROKEE PATHFINDER THIS PAGE INTENTIONALLY LEFT BLANK FAA APPROVED MAY 14, 19-73 REVISED: JULY 11, 1975 REPORT: VB-559 PAGE 3-11 MODEL: PA-28-235 CHEROKEEPA1HFINDER A. ELECTRIC PITCH TRIM INSTALLATION The following emergency information applies in case of electric pitch trim malfunction: 1. In case of malfunction, disengage electric pitch trim by pushing pitch trim switch on instrument panel to OFF position. 2. In an emergency, electric pitch trim may be overpowered using manual pitch trim. 3. In cruise configuration, malfunction results in 10° pitch change and 200 ft altitude variation. 4. In approach configuration, malfunction results in 5 ° pitch change and 50 ft altitude loss. REPORT: VB-559 PAGE 3~12 -MODEL: PA~28-23S ·· FAA APPROVED MAY 14, 1973 - ·- REVISED:-JULY l l, 1975 .. , ( B. AUTOFLITE II INSTALLATION 1. LIMITATIONS AutoFlite off for takeoff and landing. AutoFlite use prohibited above 180 mph CAS . 2. PROCEDURES a. Normal Operation CHEROKEE PATHFINDER Refer to Manufacturer's Operation Manual. b. Emergency Operation ( 1) In case of malfunction, PRESS disconne..:t switch on pilot's control wheel. (2) Rocker switch on instrument panel - OFF. (3) Unit may be overpowered manually. ( 4) In cruise configuration malfunction, 3 seconds delay results in 60° bank, and 190 ft altitude loss. (5) In approach configuration malfunction, I second delay results in 15° bank and 40 ft altitude loss. FAA APPROVED MAY 14, 1973 REVISED: JULY 11, 1975 REPORT: VB-559 PAGE 3-13 MODEL: PA-28-235 CHEROKEEPAfflFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-559 PAGE 3-14 --- - - -- - ----M6DEb: PA-28-235 - FAA APPROVED MAY 14, 1973 ) { ) '-....._ CHEROKEEPATIIFINDER C. INSTALLATION OF PIPER AUTOCONTROL III AND/OR AUTOCONTROL IIIB 1. LIMITATIONS a. Autopilot OFF during takeoff and landing. b. Autopilot use prohibited above 180 MPH CAS. 2. PROCEDURES a. PREFLIGHT '( 1) Roll Section (a) Place Radio Coupler in "Heading" mode and place A/P ON/OFF switch in the "ON" position to engage roll section. Rotate roll command knob Left and Right and observe control wheel describes a corresponding Left and Right tl,lrn, then center knob. (b) Set proper D.G. Heading on D.G. and turn Heading Indice to aircraft heading. Engage "Heading" mode switch and rotate Headin_g Indice right and left. Aircraft control wheel should turn same direction as Indice. While D.G. indice is set for a left turn, grasp control wheel and override the servo to the right. Repeat in opposite direction for right turn. (c) If VOR signal available check Omni mode on Radio Coupler by swinging Omni needle left and right slowly. Observe that control wheel rotates in direction of needle movement. (d) Disengage by placing the A/PON/OFF switch to the "OFF" position. b. IN-FLIGHT (I) Trim airplane (ball centered). (2) Check air pressure or vacuum to ascertain that the Directional Gyro and Attitude Gyro are receiving sufficient air. (3) Roll Section (a) To engage, center Roll Command Knob, place the A/P ON/OFF switch to the "ON" position. To turn rotate roll command knob in desired direction. (Maximum angle of bank should not exceed 30° .) (b) For heading mode, set Directional Gyro with Magnetic Compass. Push directional gyro HOG knob in, rotate to aircraft heading. Place the console HOG ON/OFF switch to the "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. NOTE In HOG mode the maximum bank -angles are limited to approximately 20° and single command, heading changes should be limited to 150°. (HOG Indice not more than 150 ° from actual aircraft heading.) FAA APPROVED JUNE 12, 1974 REVISED: JULY 11, 1975 REPORT: VB-559 PAGE 3-15 MODEL: PA-28-235 CHEROKEE PATHFINDER (4) VOR (a) To Intercept: 1. Using OMNI Bearing Selector, dial desired course, inbound or outbound. 2. Set identical heading on Course Selector D.G. 3. After aircraft has stabilized, position coupler mode selector knob to OMNI mode. As aircraft nears selected radial, interception and crosswind correction will be automatically accomplished without further switching. NOTE If aircraft position is less than 45 ° from selected radial, aircraft will intercept before station. If position is more than 45° , interception will occur after station passage. As the aircraft nears the OMNI station, (l/2 mile) the zone of confusion will direct an "'S" turn in alternate directions as the OMNI indicator needle swings. This alternate banking limited to the standard D.G. bank angle, is an indication of station passage. (b) To select new course: 1. To select a new course or radial, rotate the HDG indice to the desired HDG (match course). 2. Rotate OBS to the new course. Aircraft will automatically turn to the intercept heading for the new course. (c) To change stations: l. If same course is desired, merely tune receiver to new station frequency. 2. If different course is desired, position coupler mode selector to HDG mode. Dial course selector D.G. to new course. Dial OBS to new course and position coupler mode selector to OMNI mode. (5) VOR Approach Track inbound to station as described in VOR navigation section. After station passage: REPORT: VB-559 PAGE 3-16 MODEL: PA-28-235 (a) Dial outbound course on Course Selector D.G., then dial same course on OBS . (b) After established on outbound radial, position coupler mode selector to HOG mode and select outbound procedure turn heading. After 40 seconds to 1 minute select a turn in the desired direction with the Course Selector D.G. to the inbound procedure turn heading. (c) Set OBS to inbound course. ( d) When aircraft heading is 45 ° to the inbound course, dial Course Selector D.G. to inbound course and position coupler mode selector to OMNI mode. FAA APPROVED JUNE 12, 1974 CHEROKEE PATHFINDER NOTE For precise tracking over OMNI station, without "S" turn, position coupler mode selector to HOG mode just prior to station passage. If holding pattern is desired, position coupler mode selector to HOG mode at station passage inbound and select outbound heading in direction of turn. After elapsed time, dial inbound course on Course Selector O.G. When aircraft heading is 45 ° to radial, position coupler mode selector to OMNI mode. (6) LOC Approach Only (a) To intercept dial ILS outbound course on Course Selector D.G. When stabilized, position coupler mode selector to LOC REV mode. ( b) After interception and when beyond outer marker, position coupler mode selector to HDG mode and dial outbound procedure turn heading. After one minute, dial inbound procedure turn heading in direction of turn . ( c) When aircraft heading is 45° to ILS inbound course dial inbound course on Course Selector O.G. and position - coupler mode selector to LO(' NORM mode. (d) At the missed approach point (M.A.P.), or when missed approach is elected, position coupler mode selector to HOG mode and execute missed approach procedure. ( 7) LOC Approach - Back Course (Reverse) (a) To intercept dial ILS Back Course outbound heading on Course Selector O.G. When stabilized, position coupler mode selector to LOC NORM mode. ( b) After interception and when beyond fix, position coupler mode selector to HOG and dial outbound procedure turn heading. After one minute. dial inbound procedure turn heading in direction of turn. (c) When heading 45° to inbound course, dial inbound course on Course Selector D.G. and position coupler mode selector to LOC REV mode. (d) Approximately 1/2 mile from runway; position coupler mode selector to HOG mode to prevent "S" turn over ILS station near runway threshold. (e) Missed approach - same as Front Course. (See (6) d) FAA APPROVED JUNE 12, 1974 REPORT: VB-559 PAGE 3-17 MODEL: PA-28-235 CHEROKEEPA'IHFINDER c. EMERGENCY OPERATION ( l) In an emergency the Au toControl can be disconnected hy: (a) Placing the A/PON/OFF switch to the "OFF" position. (b) Pulling the Autopilot circuit breaker (aircraft with Serial Numbers 28-7610001 and up). (2) The AutoControl can be overpowered at either control wheel. (3) An Autopilot runaway, with a 3 second delay in the initiation of recovery, while operating in a climb, cruise or descending flight could result in a 60° bank and 190 foot altitude loss. (4) An Autopilot runaway, with a 1 second delay in the initiation of recovery, during an approach operation, coupled or uncoupled, could result in a 15 ° bank and 40 foot altitude loss. 3. PERFORMANCE No change. REPORT: VB-S59 PAGE 3-18 ·MODE~-:- PA-~2s~2Js FAA APPROVED JUNE 12, 1974 REVISED: DECEMBER 2, 1975 ( \ ' . ) EMERGENCY 'PROCEDURES Introduction . . . ; . . . . . . . . . Engine Power Loss During Takeoff Engine Power Loss in Flight . . . . Power Off Landing . . . . Propeller Overspeed . . . . . . Spins . . .... . . . Open Door .... . Fire .. . ..... . Loss of Oil Pressure Loss of Fuel Pressure High Oil Temperature . . Alternator Failure Engine Roughness . . . . 4-1 4-1 4-2 4-3 4-3 4-4 4-4 4-5 4-6 4-6 4-6 4-7 4-7 4-i CHEROKEE PATHFINDER EMERGENCY PROCEDURES INTRODUCTION This section contains procedures that are recommended if an emergency condition should occur during ground operation, takeoff, or in flight. 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. Since emergencies rarely happen in modern aircraft, their occurrence is usually unexpected, and the best corrective action may not always be obvious. Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise. Most basic emergency procedures, such as power off landings, are a normal part of pilot training. Although these emergencies 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. ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on circumstances. 1. If sufficient runway remains for a normal landing, land straight ahead. 2. If insufficient runway remains, maintain a safe airspeed and make only a shallow turn if necessary to avoid obstructions. Use of flaps depends on circumstances. Normally, flaps should be fully extended for touchdown. 3. If you have gained sufficient altitude to attempt a restart, proceed as follows: a. MAINTAIN SAFE AIRSPEED b. FUEL SELECTOR- SWITCH TO ANOTHER TANK CONTAINING FUEL c. ELECTRIC FUEL PUMP - CHECK ON d. MIXTURE-CHECK RICH e. CARBURETOR HEAT-ON NOTE If engine failure was caused by fuel exhaustion, power will not be regained after tanks are switched until empty fuel lines are filled, which may require up to ten seconds. If power is not regained, proceed with the POWER OFF LANDING procedure. EMERGENCYPRQCEDURES ISSUED: JULY 10, 1973 4-1 CHEROKEE PATHFINDER ENGINE POWER LOSS IN FLIGHT Complek engine power loss is usually caused by fuel flow interruption, and power will be restored shortly after fuel flow is restored. If power loss occurs at low altitude, the first step is to prepare for an emergency landing (See POWER OFF LANDING). Maintain an airspeed of at least 95 MPH IAS, and if altitude permits, proceed as follows: 4-2 1. Fuel Selector - Switch to another tank containing fuel. 2. Electric Fuel Pump - On 3. Mixture - Rich 4 . Carburetor Heat - On 5. Engine Gauges - Check for an indication of the cause of power loss. 6. Primer - Check Locked 7. If no fuel pressure is indicated, check tank selector position to be sure it is on a tank containing fuel. When power is restored: 8. Carburetor Heat - Off 9. Electric Fuel Pump - Off If the above steps do not restore power, prepare for an emergency landing. If time permits: 1. Ignition Switch - "L" then "R" then back to "BOTH." 2. Throttle and Mixture - Different settings. (This may restore power if the problem is too rich or too lean a mixture, or if there is partial fuel system restriction.) 3. Try other fuel tanks. (Water in the fuel could take some time to be used up, and allowing the engine to windmill may restore power. If power loss is due to water, fuel pressure indications will be normal.) NOTE If engine failure was caused by fuel exhaustion, power will not be regained after tanks are switched until empty fuel lines are filled, which may require up to ten seconds. If power is not restored, proceed with POWER OFF LANDING procedure. EMERGENCY PROCEDURES ISSUED: JULY 10, 1973 ( CHEROKEE PAIBFINDER POWER OFF LANDING If loss of power occurs at altitude, trim the aircraft for best iilidinll an1le, 95 MPH lAS. and look for a suilahlc field . It' measures taken to restore power arc 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 them 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 approach. When the field can easily be reached, slow up to 85 MPH IAS for the shortest landing. Excess altitude may be lost by widening your pattern, using flaps or slipping, or a combination of these. Touchdown should normally be made at the lowest possible airspeed, with full flaps. When committed to landing: 1. Ignition - Off 2. Master Switch - Off 3. Fuel Selector - Off 4. Mixture - Idle Cut-Off 5. Seat Belt (and harness if available) - Tight PROPELLER OVERSPEED Propeller overspeed is caused by a malfunction in the propeller governor, or low oil pressure, which allows the propeller blades to rotate to full low pitch. If this should occur, proceed as follows: I. THROTTLE - RETARD 2. OIL PRESSURE - CHECK . 3. PROPELLER CONTROL- FULL DECREASE RPM, THEN SET IF ANY.CONTROL IS AVAILABLE. 4. REDUCE AIRSPEED 5. THROTTLE - AS REQUIRED TO REMAIN BELOW 2575 RPM. EMERGENCY PROCEDURES REVISED: fUNE 10, 1977 4-3 CHEROKEE PATHFINDER SPINS Intentional spins are prohibited in this aircraft. If a spin is inadvertently entered, immediately use the following recovery procedures: l. THROTTLE - IDLE 2. RUDDER- FULL OPPOSITE TO DIRECTION OF ROTATION 3. CONTROL WHEEL-FULL FORWARD 4. RUDDER-NEUTRAL (WHEN ROTATION STOPS) 5. CONTROL WHEEL - AS REQUIRED TO SMOOTHLY REGAIN LEVEL FLIGHT ATTITUDE 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 bottom are remote. However, should you forget the upper latch, or not fully engage the lower latch, the door may spring partially open. This will usually happen at takeoff or soon afterward. A partially open door will not affect normal flight characteristics, and a normal landing can be made with the door open. If both upper and lower latches are open, the door will trail slightly open, and airspeed will be reduced slightly. To close the door in flight, proceed as follows: I . Slow aircraft to I 00 MPH IAS. 2. Cabin Vents - Oose 3. Stonn Window - Open 4. If upper laleh is open - latch. If lower latch is open - open top latch, push door further open, and then close rapidly. Latch top latch. A slip in the direction of the open door will assist in latching procedure. EMERGENCY PROCEDURES ISSUED: JULY 10, 1973 -...:.:.....- CHEROKEE PATHFINDER FIRE The presence of fire is noted through smoke, smell, and heat in the cabin. It 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. SOURCE OF FIRE - CHECK 1. Electrical Fire (Smoke in Cabin): a. Master Switch - Off b. Vents - Open c. Cabin Heat - Off d. Land as soon as possible. 2. Engine Fire (In Flight): a. Fuel Selector - Off b. Throttle - Closed c. Mixture - Idle Cut-Off d. Heater - Off (In all cases of fire) e. Defroster - Off (In all cases of fire) f. If terrain permits, land immediately. NOTE The possibility of an engine fire in flight is extremely remote. The procedure given above is general and pilot judgment should be the deciding factor for action in such an emergency. 3. Engine Fire (During Start): Engine fires during start are usually the result of overpriming. The following procedure is designed to draw the excess fuel back into the induction system. a. If engine has not started: (1) Mixture - Idle Cut-Off (2) Throttle - Open (3) Turn engine with starter (This is an attempt to pull the fire into the engine.) b. If engine has already started and is running, continue operating to try pulling the fire into the engine. c. In either case stated in (a) and (b), if the fire continues longer than a few seconds, the fire should be extinguished by the best available external means. d. If external fire extinguishing is to be applied: ( l) Fuel Selector Valves - Off (2) Mixture - Idle Cut-Off EMERGENCY PROCEDURES ISSUED: JULY 10, 1973 4-5 CHEROKEE PATHFINDER LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigate the 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 case, proceed toward the nearest airport, and be prepared for a forced landing. If 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 temperatures, or oil smoke, are apparent, and an airport is not close. If engine stoppage occurs, proceed to POWER OFF LANDING. LOSS OF FUEL PRESSURE 1. Electric Boost Pump - On 2. Fuel Selector - Check on full tank If problem is not an empty fuel tank, land as soon as practical and have engine-driven fuel pump checked. HIGH OIL TEMPERATURE An abnormally high oil temperature indication may be caused by a low oil level, an obstruction in the oil cooler, damaged or improper baffle seals, a defective gauge, or other causes. Land as soon as practical at an appropriate airport and have the cause investigated. A steady, rapid rise in oil temperature is a sign of trouble. Land at the nearest airport and let a mechanic investigate the problem. Watch the oil pressure gauge for an accompanying loss of pressure. EMERGENCY PROCEDURES ISSUED: JULY 10, 1973 CHEROKEE PATHFINDER ALTERNATOR FAILURE Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, insure that the reading is zero and not merely low by actuating an electrically powered device, such as the landing light. If no increase in the ammeter reading is noted, alternator failure can be assumed. 1. Reduce Electrical Load. 2. Alternator Circuit Breakers - Check 3. "Alt" Switch - Off (for 1 second), then On If the ammeter continues to indicate no output, or alternator will not stay reset, turn off "Alt" switch, maintain minimum electrical load and land as soon as practical. All electrical load is being supplied by the battery. ENGINE ROUGHNESS Engine roughness is usually due to carburetor icing and may be accompanied by serious power loss. This power loss may be evidenced by a loss of manifold pressure, 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 . Wail for a decrease in engine roughness indicating ice removal. If no change in approximately one minute. rl'tum the carburetor heat to COLD. If the engine is still rough, try steps helow: I. Mixture - Adjust for maximum smoothness. Engine will run rough if too rich or too lean. Electric Fuel Pump - On 3. Fuel Selector - Change tanks to see if fuel contamination is the problem. 4. Engine Gauges - Check for abnormal readings. If any gauge readings are abnormal, proceed accordingly. 5. Magneto Switch - "L" then "R", then back to "BOTH." If operation is satisfactory on either magneto, proceed on that magneto at reduced power, 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 cause partial melting of ice which will refreeze in the intake system; therefore when using carburetor heat, always use full heat and when ice is removed return to the full cold position. EMERGENCY PROCEDURES REVISED: NOVEMBER 9, 1973 4-7 • ) WEIGHT AND BALANCE I n U, WEIGHT AND BALANCE Log of Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-iii Weight and Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 '- Weight and Balance Data- Weighing Procedure . . . . . . . . . . . . . . . . . . . . . . . . . 5-3 Weight and Balance Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7 C. G. Range and Weight Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-8 Equipment List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11 5-i ) WEIGHT AND BALANCE FOR CHEROKEE PATHFINDER 28-741.0049 N40801 MODEL - PA-28-235 ISSUED: MAY 14, 1973 REPORT: VB-548 MODEL: PA-28-235 • ' INDEX· WEIGHT AND BALANCE Log of Revisions . . . . . . . . . . . . . . . . . Weight and Balance .............. . Weight and Balance Data - Weighing Procedure Weight and Balance Data . . .... .. ... . C. G. Range and Weight Instructions ..... . Equipment List . . . . . . . . . . . . . . . . . . A. Propellers and Propeller Accessories B. Engine and Engine Accessories ....... . . . . C. Landing Gear and Brakes . . . . . . . .. .. . D. Electrical Equipment ....... . E. Instruments . . . . . . . . . . . . . . . . . . . . . . . . F. Miscellaneous . . . . . . . . . . . . . . . . . . . . . . . G. Engine and Engine Accessories (Optional Equipment) H. Landing Gear and Brakes (Optional Equipment) I. Electrical Equipment (Optional Equipment) . J. Instruments (Optional Equipment) ... K. Autopilots (Optional Equipment) . . . . L. Radio Equipment (Optional Equipment) M. Miscellaneous (Optional Equipment) ISSUED: MAY 14, 1973 CHEROKEE PATHFINDER 5-iii 5-1 5-3 5-7 5-8 5-11 5-11 5-12 5-13 5-14 5-15 5-16 5-17 5-18 5-19 5-21 5-22 5-23 5-27 REPORT: VB-548 PAGE 5-i MODEL: PA-28-235 CHEROKEE PATHFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-548 PAGE 5-ii MODEL: PA-28-235 ISSUED: MAY 14, 1973 CHEROKEE PATHFINDER WEIGHT AND BALANCE LOG OF REVISIONS Revision Revised Pages 1 5-5 5-12 5-13 5-14 5-16 5-17 5-·19 5-26 5-27 5-28 , Title ... ' 5-l 2 5-14 5-16 5-17 5-2 I 5-22 5-23 ISSUED: MAY 14, 1973 REVISED: JUNE 12, 1974 Description and Revision Approved Date Revised Unusable Fuel. Nov. 9, 1973 Revised Oil Cooler Weight and Moment. Revised Weight, Arm, Moment and added item (b) to Nose Wheel. Revised Voltage Re~lator and Battery Weight and Moment. Removed Main Wheel Fairings and added Dual Toe Brakes. Added PAC 79399-0, Vacuum Pump. Revised Battery Weights and Moment. Revised Microphones Weights, Arms and Moments; Revised Selector Panel and Marker Beacon Weights, Arms and Moments. Revised Left and Right Adj. Seat Weights, Arms and Moments; Revised Nose and Main Wheel Fairings and Cabin Overhead Vent System Weights, Arms and Moments. Added "Cabin Overhead Vent System" and revised Weight and Moment for Ground Vent Blower. IV, :z~ ~ Added Corrosive Resistant Kit. Added PAC Approval Form. June 3, 1974 (NOTE: AIRCRAFT DELIVERED WITH MANUALS PRIOR TO THIS REVISION (»7V DO NOT REQUIRE THIS REVISION.) Added Oil Filters; added footnote. June 12, 1974 Added Annunciator Lights; added footnote. Revised Part No., Weight. Arm and Moment of Inertia Safety Belts. Add~d Oil Filter, Low Vacuum Annunciator Light and Vacuum Regulator No. 2H3- l 9: revised Vacuum Regulator No. l 33A4 Weight and Moment; added footnotes. Added Encoding Altimeter and footnote . Added AutoControl IIIB; added footnotes. Revised nomenclature (Narco Dual Comm Transceiver and King VHF Transceivers): added footnote. REPORT: VB-548 PAGES-iii MODEL: PA-28-235 CHEROKEE PATHFINDER WEIGHT AND BALANCE LOG OF REVISIONS (cont) Revision Revised Pages 3 (cont) 5-24 5-25 5-26 5-26a, 5-26b 5-27 4 5-11 5 5-5 5-15 5-19 5-21 5-23 5-27 5-28 6 5-21 5-25 5-26 5-26a REPORT: VB-548 PAGE 5-iv MODEL: PA-28-235 Description and Revision Approved Date Added footnote. Revised nomenclature (Bendix ADF, PM-I Marker Beacon, and King Audio Panel); added footnote. Revised nomenclature (Audio Selector Panel, Narco Selector Panel, Narco Comm 110 and Narco Nav 110); added footnote. /.~-L Added pages (Items for ser. nos. 75 l 0001 and up). Revised Part No., Weight and Moment of w~ Inertia Safety Belts. Added A Strap. Added F-4-13 Governor and footnote. Jan. 23, 1975 Revised C.G. equations July 11, 1975 Revised Stewart-Warner Engine Cluster Dwg. C>;f~. nos. Revised Rotating Beacon; added 67496-3 Pitch Trim and footnote. Added Engine Hour Meter (79548-0) and footnote. Revised King KX-175 ( ) VHF Transceivers' ( 1st & 2nd) Indicators' weights and moments. Added Left Adj. Seat (79591-0); added Right Adj. Se:.it (79591-1 ); added Overhead Vent System (76304-13); added Overhead Vent System with Ground Vent Blower (76304-14); relocated items to page 5-28. Added items from page 5-28; added 79337-18 Front & Rear Headrest; added Stainless Steel Control Cables. Removed Piper Dwg. No. from Clock. Dec. 2, 1975 Relocated Piper Automatic Locator to page 5-26. ~JI.Added Piper Automatic Locator relocated from page 5-25; added Dwg. No. to existing PAL Tr:.insmi tter and added second PAL Transmitter. Added King KN-61 DME; added King KN-65A DME. ISSUED: MAY 14, 1973 REVISED: DECEMBER 2, 1975 ( CHEROKEE PATHHNDER WEIGHT ANU BALANCE LO(; OF REVISIONS Revision Revised Pages De scription and Revision Approved Date 7 5-26 Added 79761-4 transmitter. June 10, 1977 1.-.. J J t~~ "177 8 5-1 Revised general Weight and Balance introductory info. March 30, 1979 f?.r,1~ 9 Title Added serial no . applicability. June 13, 1980 (NOTE: AIRCRAFT DELIVERED WITH /JJ:Jhii}.w MANUALS PRIOR TO THIS REVISION DO NOT REQUIRE THIS REVISION.) 10 5-1 Revised text info . 5-3 Revised text info. 5-7 Revised text info . 5-12 Added 20002A oil cooler. March 20, 1984 t.)«J~ ISSUED: JUNE 10, 1977 REVISED: MARCH 20, 1984 REPORT: VB-548 PAGE 5-v MODEL: PA-28-235 CHEROKEE PATHFINDER WEIGHT AND BALANCE LOG OF REVISIONS (cont) .Revision Revised Pages REPORT: VB-548 PAGE 5-vi MODEL: PA-28-235 Description and Revision Approved Date lSSUEU: JUNE IO 1977 CHEROKEE PATHFINDER WEIGHT AND BALANCE 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 th e approved envelope. The aircraft offe rs flexibility of loading. However, you cannot fill the airpla n with the maximum number of adult passengers. full fuel tanks and maximum baggage. With the flexibility comes responsibility. The pilot must ensure that the airplane is loaded within the loading envelope before he makes a takeoff. Misloading carries consequences for any aircraft. An 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. If the C.G. is too far forward in any airplane, it may be difficult to rotate for takeoff or landing. If the C.G. is too far aft, the airplane may rotate prematurely on takeoff or try to pitch up during climb. Longitudinal stability will be reduced. This can lead to inadvertent stalls and even spins; and spin recovery becomes more difficult as the center of gravity moves aft of the approved limit. A properly loaded aircraft, however. will perform as intended. Before the airplane is licensed, a basic weight and C.G. location is computed . (Basic weight consists of the empty weight of the aircraft plus the unusable fuel and full oil capacity.) Using the basic weight and C.G. location, the pilot can easily determine the weight and C.G. position for the loaded airplan e by computing the total weight and moment and then determining wh ·ther they are within the approv ed envelope. The basic weight and C.G. location for a particular airplane are recorded in the weight and balance section of the Airplane Flight Manual. 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 weight and basic C.G. position and to write these in the aircraft log book. The owner should make sure that it is done. A weight and balance calculation is necessary in determining how much fuel or baggage can be boarded so as to keep the C.G. within allowable limits. If it is necessary to remove some of the fuel to stay within maximum allowable gross weight, the pilot should not hestitate to do so. The following pages are forms used in weighing an airplane in production and in computing basic weight, basic C.G. position, and useful load. Note that the useful load includes fuel, oil, baggage, cargo and passengers. Fallowing this is the method for computing takeoff weight and C. G. ISSUED: MAY 14, 1973 REVISED: MARCH 20, 1984 REPORT: VB-548 PAGE 5-1 MODEL: PA-28-23S CHEROKEEPAfflFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-548 PAGE 5-2 - - MODEL---::P:A~28=23S ISSUED: MAY 14, 1973 ( WEIGHT AND BALANCE DATA WEIGHING PROCEDURE CHEROKEE PATHFINDER At the time of licensing, Piper Aircraft Corporation provid es e ach airplane with the licensed empty weight and center of gravity location . This data is on P age 5-7. The removal or addition of an excessive amount of equipment or excessive airplane modifications can affect the licensed empty weight and empty weight center of gravity. The following is a weighing procedure to determine this licensed empty weight and center of gravity location: 1. PREPARATION a. Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane. b. Remove excessive dirt, grease, moisture, foreign items such as rags and tools from the airplane before weighing. c. 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. d. Drain all oil from the engine, by means of the oil drain, with the airplane in ground attitude. This will leave the undrainable oil still in the system. Engine oil temperature should be in the normal operating range before draining. e. 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. f. Weigh the airplane inside a closed building to prevent errors in scale readings due to wind. 2. LEVELING a. With airplane on scales, block main gear oleo pistons in the fully extended position. b. Level airplane (see diagram) deflating nose wheel tire, to center bubble on level. ISSUED: MAY 14, 1973 REVISED: MARCH 20, 1984 REPORT: VB-548 PAGE 5-3 MODEL: PA-28-235 CHEROKEE PATHFINDER 3. WEIGHING-AIRPLANE EMPTY WEIGHT a. 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 Nose wheel (N) Right Main Wheel (R) Left Main Wheel (L) Airplane Empty Weight, as Weighed (T) 4. EMPTY WEIGHT CENTER OF GRAVITY a. The following geometry applies to the PA-28~235 airplane when airplane is level (See Item 2). ---- C.G.Arm ----~ N I -A 7R+L i----- B~ A= 8 = REPORT: VB-548 PAGE 5-4 - - -- ----MODEb:-PA~28--23S--- - - ----- - -- - Level Points (Fuselage Left Side) Wing Leading Edge The datum is 78.4 inches -ahead of the wing leading edge at the ,intersection of the straight and tapered section. ISSUED: MAY 14, 1973 l · CHEROKEEPAfflFINDER b. Obtain measurement "A" by measuring from a plumb bob dropped from the wing leading edge, at the intersection of the straight and tapered section, horizontally and parallel to the airplane centerline, to the main wheel centerline. c. Obtain measurement "B" by measuring the distance from the main wheel centerline, horizontally and parallel to the airplane centerline, to each side of the nose wheel axle. Then average the measurements. d. The empty weight center of gravity (as weighed including optional equipment and undrainable oil) can be determined by the following formula: C.G. Arm = 78.4 + A-B(N) T C.G.Arm = 78.4+( )-( )( )= ~ --0-( ---~ ) ____,;,. inches 5. LICENSED EMPTY WEIGHT -AND EMPTY WEIGHT CENTER OF GRAVITY Empty Weight (as weighed) Unusable Fuel ( 15 pints) Licensed Empty Weight ISSUED: MAY 14, 1973 REVISED: JULY 11, 1975 Weight +11.3 Arm Moment 103.0 +1164 REPORT: VB-548 PAGE 5-5 MODEL: PA-28-235 CHEROKEEPAfflFINDER THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-S48 PAGE S-6 MODEL: PA-28-235 ISSUED: MAY 14, 1973 ( - WEIGHT AND BALANCE DATA MODEL PA-28-235 CHEROKEE Airplane Serial Number ______ _ _ Registration Number _ _____ ___ Date __ _ _______ _ ___ AIRPLANE EMPTY WEIGHT CHEROKEE PATHFINDER C.G.Arm Weight X (Inches Aft - Moment - Item (Lbs) of Datum) (In-Lbs) Actual *Empty Weight Computed Unusable Fuel ( 15 pints) 11.3 103.0 1164 Standard Empty Weight Optional Equipment Licensed Empty Weight *Empty weight is defined as dry empty weight (including paint and hydraulic fluid) plus 2.4 lbs undrainable engine oil. AIRPLANE USEFUL LOAD-NORMAL CATEGORY OPERATION (Gross Weight) - Licensed Empty Weight)= Useful Load (3000 lbs) ( lbs) = lbs THIS 1.ICENSED EMPTY WEIGHT, C.G . AND USEFUL LOAD ARE FOR THE AIRPLANE AS 1.ICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE . ISSUED: MAY 14, 1973 REVISED: MARCH 20, 1984 REPORT' VB-548 PAGE 5-7 MODEL: PA-28-235 CHEROKEEPAIBFINDER C. G. RANGE AND WEIGHT INSTRUCTIONS 1. Add the weight of all items to be loaded to the licensed empty weight. 2. Use the loading graph to determine the moment of all items to be carried in the airplane. 3. Add the moment of all items to be loaded to the licensed empty weight moment. 4. Divide the total moment by the total weight to determine the C.G. location. 5. By using the figures of Item 1 and Item 4, locate a point on the C.G. range and weight graph. If the point falls within the C.G. envelope, the loading meets the weight and balance requirements. SAMPLE LOADING PROBLEM (Normal Category) Ann Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) --·- Licensed Empty Weight Oil (12 quarts) 22.5 29.1 655 Pilot and Front Passenger 340 80.5 27370 Passengers, Aft (Rear Seat) 340 118.1 40154 Fuel (82 Gal. Maximum) 95.0 Baggage 142.8 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 C.G. range and weight graph. Since this point falls within the weight - C.G. envelope, this loading meets the weight and balance requirements._ IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY. REPORT: VB-548 PAGE 5-8 ---MODEb,-P-A-::2.8-2-3 5 ISSUED: MAY 14, 1973 CHEROKEE PATHFINDER ~ WEIGHT AND BALANCE DATA MODEL PA-28-235 [:ffEROKEE Airplane Serial Number _ 2_8_-_7_4 _10_0_4_9__ _ Registration Number __N_4_0_80_1_____ Date· -------1=2--i- 2~--Z=3____ AIRPLANE EMPTY WEIGHT C. G. Arm Weight X (Inches Aft I Item (Lbs) of Datum) ~ *Empty Weight Computed 1 "" ':\ () H1 <; Unusable Fuel (15 pints) 11.3 103.0 Standard Empty Weight 1564.3 81/7 Optional Equipment l~J,o ~ 106.1 Licensed Empty Weight 170 S:3 g ~ -, - ., ' -A,:: ~ I~ 0 - Moment - (In-Lbs) 1 ?_F,F,()f_,_ 1164 127768 13501 IJ/~ li''l wt~H69 l *Em wei ht is defined as d em t wei ht 1ci u i • ( and h draulic fluid lus pty g ry p y g r ~M~ y ) p 2.4 lbs undrainable engine oil. 11'~~ AIRPLANE USEFUL LOAD-N GORY OPERATION (Gross Weight) - Licens(XJJl.c.m ) = Useful Load I f ~ 9'1,7 (3000 lbs) ( 1:. 6 lbs) = -1.908/4bs THIS LICENSED EMPTY WEIGHT, C. G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. ISSUED: MAY 14, 1973 REPORT' VB-548 PAGE 5-7 MODEL: PA-28-235 .II CHEROKEE PATHFINDER C. G. RANGE AND WEIGHT INSTRUCTIONS 1. Add the .weight of all items to be loaded to the licensed empty weight. 2. Use the loading graph to determine the moment of all items to be carried in the airplane. 3. Add the moment of all items to be loaded to the licensed empty weight moment. ' . 4. Divide the total moment by the total weight to determine the C.G. location. 5. By using the figures of Item 1 and Item 4, locate a point on the C.G. range and weight ~ ~ \ graph. If the point falls within the C.G. envelope, the loading meets the weig ht and balance J Q_} requirements. ce $"t,L e SAMPLE LOADING PROBLEM (Normal Category) )-~ 1 (JJ . Arm~( Weight Daum Moment (Lbs) I ., (Inches) (In-Lbs) .l7Qf! .,,,. gg,3 //./Q/Jf7 Licensed Empty Weight Q-2. !:: '1/ . "1'1/n. Oil ( 12 quarts) 22.5 29.1 655 Pilot and Front Passenger 340 80.5 27370 Passengers, Aft (Rear Seat) 340 118.1 40154 Fuel (82 Gal. Maximum) 492.0/ 95:0 46740 Baggage 113. 9 142.8 11.265 Total Loaded Airplane 3000.0 90.8 272453 ( The center of gravity (C.G.) of this sample loading problem is at90. 8 inches aft of the datum line. Locate this point (90. 8 ) on the C.G. range and weight graph. Since this point falls within the weight - C.G. envelope, this loading meets the weight and balance requirements. IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY. REPORT: VB-548 PAGE 5~8 ---M0DE~:-PA=-2 8-23S -------- ----- - ISSUED: MAY 14, 1973 500 450 400 350 - Cl) C z 300 ::, 0 e:. I- ::c 250 C, w ;: C <( 200 0 ...I 150 / 100 ·/ / I /j ~ 50 )½ ~ ~V 0 0 5 I 10 ISSUED: MAY 14, 1973 CHEROKEE PATHFINDER LOADING GRAPH I~ rt.,'..I I ~~~t?i .._ ~ r.:-(jj ~1/ ~<$i «."" <l~ ,, / ~ '<"o / l> 9.,<.., ,f ~ ~7~~ .~o-... / <l' q~<; / / ?-1/, ~/ I / / V , VJ ,/ / )v , / , / V V ./ " / / / V / ~e / V V ~~ / ,, ~'1, V / / V V / ,J / V / .... V ,, / V / V /'.: / ~ I ' ,, I 15 20 25 30 35 ' , 40 45 50 MOMENT/1000 (POUND ·_ INCHES) ( REPORT: VB-548 PAGE 5-9 MODEL: PA-28-235 CHEROKEE PATHFINDER 3200 , 3000 280(, Cl) C 2 2600 ::, 0 fl. 2 ....:I: 2400 CJ w 3: I 2200 I 2000 J I 1800 78 80 REPORT: VB-548 PAGE 5-10 _ _MQDEL:PA~28,,235-- C. G. RANGE AND WEIGHT t , " ~/ ~ 1/ / / / I' /" J I 82 84 86 88 90 92 INCHES AFT OF DATUM r ISSUED: MAY 14, 1973 CHEROKEE PATHFINDER EQUIPMENT LIST The following is a list of equipment which may be installed in the PA-28-235. Items marked with an "X" are items installed when the airplane was delivered by the manufacturer. Weight Arm Aft Cert. Item Item Lbs. Datum Moment Basis A. Propeller and Propeller Accessories Spinner Installation Piper Dwg. 99374 5.0 .8 4 TC 2Al3 Governor Hartzell F-4-3 ( ) or F-4-13* 5.5 9.6 53 TCP920 Propeller, Hartzell HC-C2YK-l( )F /F8468A-4 (Used with O-540-B4B5 Engine Only) 56 2.7 151 TC P920 Governor Control Piper Dwg. 67639-4 1.5 56.8 85 TC 2Al3 *Engines with serial numbers ending with "-A" require the F-4-13 governor. Other engines require the F-4-3 governor. ISSUED: MAY 14, 1973 REVISED: JANUARY 23, 1975 REPORT: VB-548 PAGE 5-11 MODEL: PA-28-235 1 CHEROKEEPAfflFINDER Item Item B. Engine and Engine Accessories Lycoming Model O-540-B4B5 Air Filter - Fram Model • CA161PL or Purolator AFP-2 Fuel Pump Engine Driven, Lycoming Dwg. 75246 Oil Cooler, Harrison* C8526250 or Niagara N.D.M. 20002A Piper Dwg. 18622 Alternator 60 Amp, Chrysler 2642997 Starter - Lycoming# 7 6211 (Prestolite MZ4206) Fuel Pump Auxiliary Piper Dwg. 65628-0 Oil Filter, Lycoming 75528 (AC •oF5578770)** Oil Filter, Lycoming '"'LW-137 43 (Cham pion '"'CH-48110)** *Included in Engine Weight. **Serial nos. 7510001 and up REPORT: VB-S48 PAGE S-12 MODEL: PA-28-235 Weight Lbs. 383.8 .. 9 1.6 1.9 12.5 * 18.0 1.8 3.3 2.8 Arm Aft Cert. Datum Moment Basis 23.4 8981 TC 295 15.1 14 TC 2A13 44.8 72 TC 295 33.4 63 TC 2Al3 14.0 175 TC 2A13 14.5 2(d TC 2Al3 113.8 205 TC 2A13 43.5 144 TC 2A13 43.5 122 TC 2A13 ISSUED: MAY 14, 1973 REVIS El-l:-M.A R(..'.ll-20.--1 ..9~4- ----- ); Item Item C. Landing Gear and Brakes _t__ Two Main Wheel Assemblies 6.00-6 (a) Cleveland Aircraft Products Wheel Assembly No. 40-86 Brake Assembly No. 30-55 (b) Two Main 6-Ply Rating Tires 6.00-6 with Regular Tubes X One Nose Wheel 6.00-6 (a) Cleveland Aircraft Products Wheel Assembly No. 40-76B (Less Brake Drum) (b) One Nose Wheel 4-Ply Rating Tire 6.00-6 with Regular Tube ISSUED: MAY 14, 1973 REVISED: NOVEMBER 9, 1973 Weight Lbs. 33.9 12.8 CHEROKEE PATHFINDER Arm Aft Cert. Datum Moment Basis 109.6 3715 TC 2A13 32.0 410 TC 2A13 REPORT: VB-548 PAGE 5-lJ MODEL: PA-28-235 CHEROKEE PATHFINDER Item Item D. Electrical Equipment Stall Warning Device, Safe '1-- Flight In strument Corporation No. C5 2207-4 7' Voltage Regulator, Wico Electric No. X-16300B Battery 12V, 25 A.H., Rebat Model S-25 ~ Overvo.ltage Relay, Wico Electri No. 16799 REPORT: VB-548 PAGE 5-14 MODEL: PA -28-235 Weight Lbs. .2 .9 21.9 .5 Arm Aft Cert. Datum Moment Basis 80.2 16 TC 2Al3 51.9 47 TC 2Al3 168.0 3679 TC 2Al3 55.4 28 TC 2Al3 ISSUED: MAY 14, 1973 REVISED: NOVE MB E R9 , 1973 Item Item E. Instruments Compass -Piper Dwg. 67462 Airspeed Indicator, Piper Dwg. 63205-3 or -14 Tachometer, Piper Dwg. 62177 Altimeter, Piper PS50008-2 or -3 Engine Cluster, Stewart-Warner, Piper Dwg. 95241-11 Engine Cluster, Stewart-Warner, Piper Dwg. 95241-15 Manifold Pressure Gauge, Piper PS50031-3 or 4 ISSUED: MAY 14, 1973 REVISED: JULY 11, 1975 Weight Lbs. .9 .6 .7 1.0 .8 .8 .9 CHEROKEEPATIIFINDER Arm Aft Cert. Datum Moment Basis 59.9 54 TC 2A13 61.8 37 TC 2A13 61.2 43 TC 2A13 60.9 61 TC 2A13 62.4 50 TC 2A13 62.4 50 TC 2A13 60.8 55 TC 2A13 REPORT: VB-548 PAGE 5-15 MODEL: PA-28-235 CHEROKEE PATHFINDER Item Item F. Miscellaneous Forward Seat Belts (2) Piper PS50039-4-2A Inertia Safety Belts, Front (2), Piper PS50039-4-l 7 Rear Seat Belts (2) PS50039-4-3 Flight Manual & Logs Toe Brakes (Dual) Piper Dwg. 63473 Tow Bar, Piper Dwg. 99458 REPORT: VB-548 PAGE 5-16 MODEL: PA-28-235 Weight Lbs. 1.5 1.5 1.4 2.6 11.0 1.3 Ann Aft Datum 81.9 119.6 123.0 95.1 49.6 161.7 Cert. Moment Basis 123 TSO C22 179 TC 2A13 172 TSO C22 247 TC 2A13 S46 TC 2A13 210 TC 2Al3 ISSUED: MAY 14, 1973 REVISED: JUNE 12, 1974 f Item Item G. Engine and Engine Accessories (Optional Equipment) Vacuum Pump, Airborne Mfg. L Co., Model No. 200cc and Drive l Oil Filter, Lycoming "75528 (AC•OF5578770) ~ Vacuum Regulator, Airborne Mfg. Co., No. l 33A4 X. Vacuum Filter, Piper Dwg. 66673 ' Vacuum Pump, Airborne Mfg. ~ Co-., Model 211cc and Drive, PAC 79399-0 lSSUED: MAY 14, 1973 REVISED: NOVEMBER 9, 1973 Weight Lbs. 5.0 3.3 .7 .3 3.2 CHEROKEE PATHFINDER Arm Aft Cert. Datum Moment Basis 40.0 200 TC 2Al3 43.5 144 TC 2Al3 52.0 36 TC 2Al3 52.0 16 TC 2Al3 40.0 128 TC 2Al3 REPORT: VB-548 PAGE 5-17 MODEL: PA-28-235 CHEROKEE PATHFINDER Item Item H. Landing Gear and Brakes (Optional Equipment) One Nose Wheel 6.00-6 6-Ply Rating Tube (a) Cleveland Aircraft Products Wheel Assembly No. 38501 • (Less Brake Drum) REPORT:.VB'!S48 PAGE S-18 MODEL: PA-28-235 Weight Arm Aft Cert. Lbs. Datum Moment Basi s 12.5 30.4 380 TC 2Al3 l. : . ISSUED: MAY-14, 1973 CHEROKEE PATHFINDER ( Weight Arm Aft Cert. Item Item Lbs. Datum Moment Basis I. Electrical Equipment (Optional Equipment) Rotating Beacon 1.5 263.4 395 TC 2A13 Landing Light, G.E. Model 4509 .5 13.1 7 TC 2A13 Navigation Lights (2) Grimes Model Al285 (Red and Green) .4 106.6 43 TSO C30b Navigation Light (Rear) ( 1) Grimes Model 2064- (White) .2 281.0 56 TSO C30b Battery 12V, 35 A.H. Rebat R-35 (Weight 27.2 lbs) 5.3 168.0 890 TC 2A13 Cabin Light, Piper Dwg. 95229 .3 99.0 30 TC 2A13 Cabin Speaker SB-15052 or 6EU 1937, Quincy Speaker Co., Oakton, Indiana .8 99.0 79 TC 2A13 Auxiliary Power Receptacle, Piper Dwg. 62225 2.7 178.5 482 TC 2A13 External Power Cable Piper Dwg. 62355-2 4.6 142.8 657 TC 2A13 Pjper Pitch Trim Piper Dw_g. 67496-2, -3* 4.3 155.3 668 TC 2Al3 Heated Pitot Head Piper Dwg. 65797-5 .4 263.4 105 TC 2Al3 Anti-Collision Lights Whelen Engineering Co. Piper Dwg. 99033-2 or-5 Power Supply Model HS No. A412A-14 (with Fin Light only) 2.3 198.0 455 TC 2A13 \ *Serial nos. 28-7510028 and up ISSUED: MAY 14, 1973 REPORT: VB-548 PAGE 5-19 REVISED: JULY 11, 197 5 MODEL: PA-28-235 Cl:IEROKEEPATHFINDER Item Item I. Electrical Equipment (Optional Equipment) (cont) Light, Fin Tip A470 Cable, Fin Light A417-l/151 Power Supply Model HD T3 No. A413 (with Fin and Wing Lights) Lights, Wing Tip (2) (0.15 lbs each) No. 429 PR or PG Cable Wing Lights A417-1/388 & A417-1/326 REPORT: VB-S48 PAGE S-20 MODE L: PA-28-23S Weight Lbs. .4 .4 3.0 .3 2.0 Arm Aft Cert. Datum Moment Basis 263.4 105 TC 2Al3 230.7 92 TC 2Al3 198.0 594 TC 2Al3 106.6 32 TC 2A13 115.6 231 TC 2Al3 ISSUED: MAY 14, 1973 ( CHEROKEE PATHFINDER it Weight Arm Aft Cert. Item Item Lbs. Datum Moment Basis J. Instruments (Optional Equipment) Suction Gauge. Piper Dwg. 99480-0 or -2 .5 62.2 31 TC 2Al3 Vertical Speed, Piper Dwg. 99010-2. -4 or -5 1.0 60.9 61 TC 2A13 Vertical Speed , Piper Dwg. 99010-3 .5 62.2 31 TC 2Al3 Attitude Gyro , Piper Dwg. 99002-2, -3. -4 or -5 2.2 59.4 131 TC 2A13 Directional Gyro. Piper Dwg. 99002-2, -3. -4 or -5 2.6 59.7 155 TC 2A13 Air Temperature Gauge Piper Dwg. 99479-0 or -2 .2 72.6 15 TC 2Al3 Clock .4 62.4 25 TC 2Al3 Tru-Speed Indicator. - --- - Piper Dwg. 62143-3 or -14 ( same as Standard Equipment) TC 2Al3 Turn and Slip Indicator. Piper PS50030-2 or -3 2.6 59.7 155 TC 2A13 Exhaust Gas Temperature Gauge, Piper Dwg. 99026 .7 55.4 39 TC 2A13 Encoding Altimeter Piper PS50008-6 or -7 * .9 60.3 54 TSO Cl Ob C88 Engine Hour Meter** Piper Dwg. 79548-0 .3 61.2 18 TC 2A13 *Weight and moment difference between standard and optional equipment. **Serial nos. 28-7610001 and up. ISSUED: MAY 14, 1973 REVISED: DECEMBER 2, 1975 REPORT: VB-548 PAGE 5-21 MODEL: PA-28-235 CHEROKEEPATIIFINDER Item Item K. Autopilots (Optional Equipment) AutoControl III* RollServq, •tC363-l-183R Console *IC338 (thru S/N 9999) Cables Attitude Gyro• 52D66 Directional Gyro• 52D54 Omni Coupler• l C388 AutoFlite II Roll Servo • l C363-I -l 83R Cable Panel Unit• 52D75-3 or -4 AutoControl III B • * Roll Servo• 1c363-I-183R Console • IC338 (S/N 10000 &. up) Cables Attitude Gyro, • 52D66 Directional Gyro, • 52D54 Omni Coupler,• tc388 "'Serial nos. 7 4 I 000 l through 7410 I 20 "'* Serial nos. 7 510001 and up REPORT: VB-548 PAGE 5-22 MODEL: PA-28-235 Weight Lbs. 2.5 1.2 .7 2.3 3.2 .9 2.5 .7 2.4 2.5 1.0 .5 2.7 2.9 1.0 Ann Aft Cert. Datum Moment Basis 122.2 306 STC SA l 406SW 60.l 72 STC SA 1406SW 95.5 67