Piper Cherokee 235 'B' Airplane Owner's Handbook

The Piper Cherokee 235 B is a single-engine, four-seat, high-wing general aviation aircraft. It is equipped with a Lycoming O-540-B engine rated at 235 horsepower. The aircraft has a standard fuel capacity of 84 gallons and a maximum baggage weight of 200 pounds. The 235 B is known for its good handling and performance. It is a popular choice for flight training, personal transportation, and recreational flying.

PDF Download

Document

msma

CHEROKEE 235 B'

OWNER'S HANDBOOK

WARNING

The rudder pedals are suspended from a torque tube which extends across the fuselage. The pilot should become familiar with the proper positioning of his feet on the rudder pcdais so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes. 757 436

tfa

CHEROKEE 235 "S'

Owner's H a n d b o o k mmm

Piper Aircraft Corporation, Vero Beach, Florida

U.S.A.

/ / a non-conformity of information should exist be- tween this manual and the FAA Approved Flight

Manual, the Flight Manual shall be considered the authority.

Additional copies of this manual, Part

No. 753 729, may be obtained from your

Piper Dealer.

Published by

PUBLICATIONS DEPARTMENT

Piper Aircraft Corporation

753 729

Issued; July 1966

Revised: February 1968

as&s****

S%11

'•.-'-' • sfr.v •Wi<?K'J*

" v ?;:-• i',

'-'• r j - *V,'"V* ^

/- t v J i " V J " '* *J

' - • ' , .

''vWi'V, f V

• • • . > IP

' v .

JSte^lsMs

§§

. i i n

SECTION I

SPECIFICATIONS

Performance . 1

Weights 2

Power Plant , 2

Fuel and Oil 3

Baggage 3

Dimensions .

, , .

.

. 3

Landing Gear 3

CHEROKEE 235 " B " SECTION

SECTION I

SPECIFICATIONS

PERFORMANCE

Performance figures are for standard airplanes flown at gross weight under standard conditions at sea level, or stated altitude.

Any deviation from standard equipment may result in changes in performance.

Take-off Run (ft) (flaps up)

PA-28-235

(Fixed Pitch)

935

PA-28-235

(Const, Speed)

810

Take-off Distance Over 50~ft

Obstacle (ft) (flaps up)

Take-off Run (ft) (flaps 25°)

Take-off Distance Over 50-ft

1510

800

Obstacle (ft) (flaps 25°)

Absolute Ceiling

1360

Best Rate of Climb Speed (mph) 100

Rate of Climb (ft per min) 825

Service Ceiling (ft) 14,500

16,500

Top Speed (mph)

Cruising Speed (75% power, sea level mph)

Optimum Cruising Speed (75% power, 7000 ft, mph)

Fuel Consumption (gal per hr

166

146

156

75%)

Cruising Range (75% power,

14.0

1350

750

1220

100

900

16,500

18,500

164

145

154

14.0 s e a level, mi) 875 870

660701 1

SECTION CHEROKEE 235 " B *

SPECIFICATIONS (cont):

KhUKMANCL

Cruising Range (75% power,

7000 ft) (mi)

Optimum Cruising Range

(55% power, 10,000 ft)

Stalling Speed (flaps down, mph)

Stalling Speed (flaps up,mph)

Landing Roll (flaps down, ft)

Landing Distance Over 50-ft

Obstacle (ft)

PA-28-235

(Fixed Pitch)

935

1130

680

1300

PA-28-235

(Const. Speed)

923

1105

680

1300

WEIGHTS

Gross Weight (lbs)

Empty Weight (Standard) (lbs)

USEFUL LOAD (Standard)(lbs)

2900

1435

1465

2900

1460

1440

POWER PLANT

Engine - Lycoming

Rated Horsepower

Rated Speed (rpm)

Bore (inches)

Stroke (inches)

Displacement (cubic inches)

Compression Ratio

Dry Weight (pounds)

Propeller

O-540-B4B5

235

2575

5.125

4.375

541.5

7.2:1

395

1P235PFA80

O-540-B4B5

235

2575

5.125

4.375

541.5

7.2:1

395

HC-C2YK-1

2 660701

CHEROKEE 235 " B " SECTION

SPECIFICATIONS (cont):

FUEL AND OIL

Fuel Capacity (main tank) (U.S. gal)

Fuel Capacity (auxiliary tanks) (U.S. gal) 34

Oil Capacity (U.S. qts) 12

Fuel, Aviation Grade (tnin octane) 80/87

BAGGAGE

Maximum Baggage (lbs) 200

Baggage Space (cubic ft) 24

Baggage Door Size (in) 20 x 22

DIMENSIONS

Wing Span (ft) 32.0

Wing Area (sq ft) 170

Wing Loading (lbs per sq ft) 17.0

Length (ft) 23.7

Height (ft) 7.1

Power Loading (lbs per hp) 12.4

LANDING GEAR

Wheel Base (ft) 6.2

Wheel Tread (ft) 10.0

Tire Pressure (lbs) Nose 28-30

Main 3 5-40

660701

SECTION I CHEROKEE 235 " B "

63.0*

10'

23' 8.55"

V 5.0"

680220

SECTION II

DESIGN INFORMATION

Engine and Propeller 5

Structures 6

Landing Gear 7

Control System . 7

Fuel System . 8

Electrical System 9

Heating and Ventilating System . * . a . 11

Cabin Features 11

CHEROKEE 235 " B " SECTION II

ENGINE AND PROPELLER

The Lycoming 0-540-B 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. The 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 system constructed of heavy gauge stainless steel which incorporates two heater shrouds, one for cabin heat and the other for carburetor deicing.

The propeller used on the PA-28-235 is either the McCauley

1P235PFA80 fixed pitch aluminum alloy unit or the Hartzell

HC-C2YK-1/8468A-4 constant speed propeller.

The McCauley propeller is 80 inches in diameter, with a standard pitch of 69 inches, although propellers with a pitch from

66 inches to 71 inches may be installed for s p e c i a l purposes.

All performance figures are based on the standard 69 inch propeller.

The Hartzell propeller is 80 inches in diameter, and is controlled by a Hartzell F-4-3 governor 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 cockpit.

The two-piece cowling on the Cherokee is designed to cool the engine in all normal flight conditions, including protracted climb, without the use of cowl flaps or cooling flanges.

The throttle is of the push-pull type and is located in the

66070! 5

SECTION II CHEROKEE 235 " B "

lower center of the instrument panel. A knurled friction lock is provided to prevent creeping of the throttle from any desired position. The mixture control, located in the lower right hand side of the instrument panel, is a push-pull control like the throttle.

The full rich position is obtained when the control is full forward, while the full aft position provides an idle cut-off for stopping the engine. Intermediate positions are used for leaning the mixture at altitudes above sea-level. The carburetor heat control, located to the left of the throttle, provides maximum carburetor heat when pulled to its full aft position. With carburetor heat off, a l l engine air passes through a high-efficiency dry-type filter.

Therefore, prolonged ground operation with carburetor heat"ON

M should be avoided, particularly on unimproved fields as the air is not filtered.

STRUCTURES

All structures are of aluminum alloy construction and are designed to ultimate load factors well in excess of normal requirements, All exterior surfaces are primed with etching primer and painted with acrylic enamel.

The wings are attached to each side of the fuselage by inserting 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 laminar flow type, NACA

650^415 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 s e a t .

6 660701

CHEROKEE 235

B " SECTION II

LANDING GEAR

The landing gears use a Cleveland 600 x 6 wheel, the main wheels being provided with brake drums and single disc hydraulic brakes. The nbse wheel carries a 600 x 6 four ply rating tire with tubes while the main gear uses 600 x 6 six ply rating tires.

The nose gear is steerable through a 30 degree arc each side of neutral by use of the rudder pedals. A spring device is incorporated in the rudder pedal torque tube assembly to aid in rudder centering and to provide rudder trim. The nose gear steering mechanism also incorporates a hydraulic shimmy dampener,

The oleo struts are of the air-oil type, with normal.extension being 3-1/4 inches for the nose gear and 4-1/2 inches for the main gear under normal static load (empty weight of airplane plus full fuel and oil).

The brakes are actuated by a hand lever and master cylinder located below and behind the left center of the instrument subpanel. The brake-fluid reservoir is installed on the top, left, front face of the firewall. 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 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.

CONTROL SYSTEM

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 slap type, with an anti-servo tab which also acts as a longitudinal trim tab, actuated by a control mounted on the control tunnel between

Stabilator Trim Control

680220 7

SECTION II CHEROKEE 235

, J

B "

the two front s e a t s . The stabilator provides extra stability and controllability with less s i z e , drag and weight than conventional tail surfaces. The ailerons are providedwith 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 pastcenter 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, s o it must be completely retracted when used as a step. The flaps have three extended positions, 10, 25 and 40 degrees.

FUEL SYSTEM

Standard fuel capacity of the Cherokee is 84 gallons, all of which is usable except for approximately one pint in each of the four tanks. The two main inboard tanks, which hold 25 gallons each, are attached to the wing structure with screwsand nutplates and may be easily removed for service or inspection. The tip tanks are constructed of resin-impregnated fiberglas and hold 17 gallons each.

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 " O F F " position. When using l e s s than the standard 84 gallon capacity of the tanks, fuel should be distributed equally between each side and may

Fuel Drain Lever be placed in either the in-

8 660701

CHEROKEE 235 " B " SECTION II

board or tip t a n k s .

Each fuel tank i s 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. This strainer should be drained regularly to avoid the accumulation of water or sediment. The drain valve is operated by pressing DOWN on the lever located on the right hand s i d e of the cabin below the forward edge of the rear s e a t .

Fuel quantity gauges for each of the four tanks are located in the engine gauge cluster on the right 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 switch and should be " 0 N

for all take-offs and landings.

ELECTRICAL SYSTEM

The Cherokee is equipped with a 12 volt, 60 ampere alternator which provides electrical power at all engine s p e e d s and results in improved performance for radio and electrical equipment and longer battery life.

In addition to the alternator, the electrical system includes a 25 ampere-hour battery, a voltage regulator and a master switch relay. The battery and relay are mounted immediately aft of the baggage compartment. Access for service or inspection is obtained through a removable panel adjacent to the baggage door.

The battery box i s designed to accommodate a larger capacity battery for extreme cold weather operation.

Electrical switches, fuses and fuse spares are located on the lower left side of the instrument panel.

Standard electrical a c c e s s o r i e s , in addition to those already listed, include a starter, stall warning indicator, cigar lighter and ammeter. Navigation lights, anti-collision light, landing light, instrument lighting and a cabin dome light are offered as

680220 9

SECTION II CHEROKEE235 " B "

optional accessories.

Circuit provisions are made to handle optional communications and navigational equipment. In the event either the 5 ampere or 60 ampere circuit breaker should open in flight, reduce the load on the alternator by turning off all unnecessary electrical equipment first, turn off the master switch, reset either or both circuit breakers, turn on master switch and observe ammeter for normal indication while turning on the required electrical equipment. In airplanes with serial numbers 28-10763 and up, an overvoltage relay protects electrical equipment from surges over

16.5 volts and from regulator failure. If overvoltage occurs, the relay will open and the ammeter will indicate " 0 " output from alternator. Reset the relay by turning the master switch to " O F F " for one minute, then turn the master switch to " O N " . If overvoltage persists after recyclingthe master switch, continue flight by monitoring the voltmeter and reducing the battery load to a minimum.

In conventional generator systems, the ammeter indicates battery discharge. In the Cherokee electrical system, the ammeter displays the load in amperes placed on the system at any given time. With all electrical equipment except the master switch in the " O F F " position, the ammeter will indicate the amount of charging current demanded by the battery. This amount will vary and depends on the percentage of full charge on the battery at the time. When the battery becomes charged, the current displayed on the ammeter will reduce to a minimum value of about two amperes. As each unit of electrical equipment is switched on the amount of current it draws will be shown on the ammeter.

The maximum continuous load for night flight with all equipment on is approximately thirty amperes. This thirty amperes plus approximately two amperes for the fully charged battery will appear continuously under these flight conditions.

Because of the mechanical simplicity of the alternator, maintenance should prove to be a minor factor a s compared to previous systems. Should service be required, contact your local

Piper dealer.

10 680220

CHEROKEE 235 " B " SECTION II

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 s e c t i o n s . A large adjustable outlet i s located on the side of the cabin near the floor at each s e a t location. Air is exhausted through an outlet under the rear s e a t ,

CABIN FEATURES

The instrument panel of the Cherokee i s designed to accommodate the customary advanced flight instruments and a l l the normally required power plant instruments. The Artificial Horizon,

Directional Gyro and the Turn and Bank instruments are vacuum operated through use of a vacuum pump installed on the engine.

A natural separation of the flight grQup and the power group is provided by placing the communications and radio navigational equipment in the center of the panel.

The cabin interior includes double side windows, two sun visors, cabin dome light, ash trays, two map pockets and pockets on the backs of each front s e a t . The front s e a t s are adjustable fore and aft for pilot-passenger comfort and ease of entry and exit. Recessed arm r e s t s are also provided for the front s e a t s .

The 24 cubic foot baggage area which includes a roomy hat shelf may be reached from the cabin or through a large 20 x 22 inch outside door.

680220 11

•WHEN CONSTANT SPEED

IS I N S T A L L E D .

1 7 .

1 8 .

1 9 .

2 0 .

' 2 1 .

2 2 .

2 3 .

2 4 .

20 19

THROTTLE CONTROL 3 0 .

AUDIO SELECTOR 3 1 .

STARTER

MASTER S W I T C H

CHEROKEE 235

B " SECTION II

CABIN FEATURES

The instrument panel of the Cherokee is designed to accommodate the customary advanced flight instruments and all the normally required power plant instruments. The Artificial Horizon,

Directional Gyro and the Turn and Bank instruments are vacuum operated through use of a vacuum pump installed on the engine.

A natural separation of the flight group and the power group is provided by placing the communications and radio navigational equipment in the center of the panel.

The cabin interior includes double side windows, two sun visors, cabin dome light, ash trays, two map pockets and pockets on the backs of each front s e a t . The front seats are adjustable fore and aft for pilot-passenger comfort and ease of entry and exit. Recessed arm rests are also provided for the front s e a t s .

The 24 cubic foot baggage area which includes a roomy hat shelf may be reached from the cabin or through a large 20 x 22 inch outside door.

660701 13

SECTION III

OPERATING INSTRUCTIONS

Preflight 14

Starting Engine . 1 5

Warm-Up . 16

Ground Check . . . » 17

Take-Off . 1 8

Climb 18

Stalls . 19

Cruising 19

Approach and Landing 20

Mooring. 21

Weight and Balance . 21

Fuel System Operating Procedures 22

SECTION II CHEROKEE 235

B "

SECTION II

OPERATING INSTRUCTIONS

PREFLIGHT

The airplane should be given a thorough visual inspection prior to each flight. Particular attention should be given to the following items in the illustration below:

1. a. Master switch " O N " . b. Check fuel quantity indicators (four tanks). c. Depress sump drain knob for four or five seconds to drain possible accumulation of water and sediment.

1 » j

-4

) *

1 \ i w

\ *

M .

: - - - < - - - - 2 - - < - - / J

•» V f

'••A

' — »

\ - * - 2 i

I n _

Wa. --'

Y\ ,,----4-

» -

1 1 1 1

)

;

— - J

» - * - -

1 i

±

14 660701

SECTION III CHEROKEE 235 " B "

d. Master switch and ignition " O F F " .

2. a. Check for external damage, operational interference of control surfaces or hinges. b . Insure that wings and control surfaces are free of snow, ice or frost.

3. a. Visually check fuel supply, secure c a p s . b. Drain fuel tank sumps. c . Check navigation lights.

4. a. Visually check fuel supply, secure c a p s . b. Drain fuel tank sumps. c. Check that fuel system vents are open. d. Check landing gear shock struts for proper inflation. e. Check tires for cuts, wear and proper inflation.

5. a. Inspect windshield for cleanliness. b. Check the propeller and spinner for defects or nicks. c. Check for obvious fuel or oil leaks. d. Check oil level, 8 quarts minimum. (Insure dipstick is properly seated.) e . Inspect cowling and inspection covers for security. f. Check nose wheel tire for inflation, wear. g. Check nose wheel shock strut for proper inflation.

6. a. Stow tow bar and control locks, if used. b. Check baggage for proper storage and security. c. Close and secure the baggage compartment door.

7. a. Upon entering aircraft ascertain that all primary flight controls operate properly. b. Close and secure the cabin door. aircraft. c. Check that required papers are in order and in the

STARTING ENGINE

After completion of the preflight inspection:

1. Lock the wheel brakes.

2. Set the carburetor heat control in the full " C O L D " position.

660701

CHEROKEE 235

B

SECTION III

3. Set propeller control in full " i n c r e a s e RPM"-

4- Select the desired tank with the fuel valve.

5. Move the mixture to the full " R I C H " position.

6. Open the throttle 1/8 to 1/4 inch.

7. Turn the electric fuel pump " O N " .

In cold weather (below 40 degrees F.) prime the engine with one to three full strokes of the priming pump. If extremely cold, starting will be aided by pulling the propeller through by hand

(switch " O F F " ) four to five revolutions. If the temperature i s above 40 degrees the engine may be primed by three or four short quick strokes of the throttle.

After priming, turn the electric master switch on, engage the starter and allow the engine to turn approximately one full revolution, then turn the ignition switch to the " L e f t " magneto position.

When the engine is firing evenly, turn the magneto switch to the " B o t h " position and advance the throttle to 800 RPM. Check the oil pressure gauge for a pressure indication. If oil pressure i s not indicated within thirty seconds, stop the engine and determine the trouble.

If the engine fails to start at the first attempt, another attempt should be made without priming. If this fails, it is possible that the engine is over primed. Turn the magneto switch off, open the throttle slowly, and rotate the engine approximately ten revolutions with the starter. Reprime the engine with one half the amount used in the initial attempt, turn the magneto switch to

" L e f t " , and repeat the starting procedure. If the engine again fails to start, refer to the "Lycoming Operating Handbook,

Engine Troubles and Their Remedies".

WARM-UP

As soon a s the engine starts, the oil pressure should be checked. If no pressure is indicated within thirty seconds, slop the engine and determine the trouble. In cold weather it will

660701 16

SECTION III CHEROKEE 235

J 3

B "

take a few seconds longer to get an oil pressure indication.

Warm-up the engine at 800 to 1200 RPM.

Take-off may be made as soon as ground check is completed, providing that the throttle may be opened fully without back firing or skipping, and without reduction in engine oil pressure.

GROUND CHECK

The magnetos should be checked at 1800 RPM on airplanes with a fixed pitch propeller or at 2150 RPM with propeller set at high RPM on airplanes with a constant speed propeller. Switch from both magnetos to only one and note the RPM loss; switch to the other magneto and again note the RPM loss. Drop off on either magneto should not exceed 125 RPM.

Check both the oil temperature and pressure. The temperature may be low for some time if the engine is being run for the first time of the day, but as long as the pressure is within limits the engine is ready for take-off.

The propeller control should be moved through its complete range to check for proper operation, and then placed in full " i n c r e a s e RPM" for take-off. To obtain maximum RPM with the vernier control, push the control forward while depressing the button, and then rotate the vernier control clockwise until it contacts the stop.

In cold weather, the propeller control should be cycled at least three times, to assure that warm engine oil has circulated through the system.

Carburetor heat should also be checked prior to take-off to be sure thai the control is operating properly and to clear any ice which may have formed during taxiing,

17 660701

CHEROKEE 235 " B

t #

SECTION III

TAKE-OFF

J u s t before take-off the following items should be checked:

1. Controls free 6. Carburetor heat " O F F "

2. F l a p s " U P " 7. Fuel on proper tank

3. Tab set 8. Electric fuel pump " O N "

4. Propeller set 9. Engine gauges normal

5. Mixture " R I C H " 10. Door latched

11. Altimeter set

The take-off technique is conventional for the Cherokee.

The tab should be set slightly aft of neutral, with the exact setting determined by the loading of the aircraft. Allow the airplane to accelerate to 55 to 65 miles per hour, then e a s e back on the wheel enough to let the airplane fly itself off the ground-

Premature raising of the nose, or raising it to an excessive angle, will result in a delayed take-off. After take-off let the aircraft accelerate to the desired climb speed by lowering the nose slightly.

Take-offs are normally made with flaps up, to simplify operating procedure. However, for short field take-offs, and for take-offs under difficult conditions such as in deep grass or on a soft surface, distances can be reduced appreciably by lowering flaps t o 25° (second notch).

CLIMB

The best rate of climb at gross weight will be obtained at

100 miles per hour. The best angle of climb may be obtained at

90 miles per hour. At lighter than gross weight these speeds are reduced somewhat.For climbing enroute a speed of 115 miles per hour is recommended. This will produce better forward speed and increased visibility over the nose during the climb.

660701 18

SECTION III CHEROKEE 235 " B '

STALLS

The stall characteristics of the Cherokee are conventional.

Visual stall warning i s provided by a red light located on the left side of the instrument panel which is turned on automatically between 5 and 10 miles per hour abovethe stall speed. The gross weight stalling speed of the Cherokee with power off and full flaps is 60 miles per hour. With the flaps up this speed is increased 10 miles per hour,

Intentional spins are prohibited in this airplane. In the event that an inadvertent spin occurs, standard recovery technique should be used immediately.

CRUISING

The cruising speed of the Cherokee is determined by many factors including power setting, altitude, temperature, loading, and equipment installed on the airplane.

The normal cruising power is 75% of the rated horsepower of the engine. True airspeeds, which may be obtained at various altitudes and power settings, can be determined from the charts in "Section IV" of this handbook.

Use of the mixture control in cruising flight reduces fuel consumption significantly, especially at high altitudes. The mixture should always be leaned during cruising operations at

75% power or l e s s , but during the climb only at altitudes above

5000 feet.

When selecting cruising RPM below 2300, limiting manifold pressure for continuous operation, as specified by the Lycoming

Operators Manual, should be observed.

The continuous use of carburetor heat during cruising flight decreases engine efficiency. Unless icing conditions in the carburetor are severe, do not cruise with the heat on. Apply full carburetor heat slowly and only for a few seconds at intervals determined by icing severity.

In order to keep the airplane in best lateral trim during

19 660701

CHEROKEE 235 " B " SECTION III

cruising flight, the fuel should be used alternately from each main tank, and when they are exhausted, from each tip tank. It is recommended that one main tank be used for one hour after takeoff; the other main tank used until nearly exhausted, then return to the first main tank. When nearly exhausted, turn to one tip tank and alternate at one-half hour intervals to maintain lateral trim.

APPROACH AND LANDING

Before landing check list:

1. Mixture " R I C H "

2. Propeller set

3. Carburetor heat " O F F " (unless icing conditions exist)

4. Electric fuel pump " O N "

5. Fuel selector on proper tank

6. Flaps as desired (under 115 M.P.H.)

The airplane should be trimmed to an approach speed of about 90 miles per hour and flaps extended. The flaps can be lowered at speeds up to 115 miles per hour, if desired. The propeller should be set at full RPM or at a high cruising RPM to facilitate an emergency go-around if needed. Carburetor heat should not be applied unless there is an indication of carburetor icing, since the use of carburetor heat causes a reduction in power which may be critical in case of a go-around. Full throttle operation with heat on is likely to cause detonation.

The amount of flap used during landings and the speed of the aircraft at contact with the runway should be varied according to the landing surface and existing conditions, both windwise and loadwise. It i s generally good practice to contact the ground at the minimum possible safe speed consistent with existing conditions.

Normally, the best technique for short and slow landings i s to use full flap and enough power to maintain the desired airspeed and approach flight path. Mixture should be full rich, fuel on the fullest tank,carburetor heat off, and electric fuel pump on.

660701 20

SECTION III CHEROKEE 235 " B "

Reduce the speed during the flareout and contact the ground close to the stalling speed (55 to 65 MPH). After ground contact hold the nose wheel off as long as possible. As the airplane slows down, drop the nose and apply the brakes. There will be less chance of skidding the tires if the flaps are retracted before applying the brakes. Braking is most effective when back pressure is applied to the control wheel, putting most of the aircraft weight on the main wheels. In high wind conditions, particularly in strong crosswinds, it may be desirable to approach the ground at higher than normal speeds with partial or no flaps.

MOORING

The Cherokee should be moved on the ground with the aid of the nose wheel tow bar provided with each plane and secured in the baggage compartment. Tie downs may be secured to rings provided under each wing, and to the tail skid. The aileron and stabilator controls should be secured by looping the safety belt through the control wheel and pulling it tight. The rudder is held in position by its connections to the nose wheel steering, and normally does not have to be secured. The flaps are locked when in the full up position, and should be left retracted.

WEIGHT AND BALANCE

It is the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs. center of gravity envelope while inflight. For weight and balance data see the Airplane Flight Manual and Weight and Balance form supplied with each airplane.

21 680220

CHEROKEE 235 " B " SECTION III

FUEL SYSTEM OPERATING PROCEDURES

1. Fuel quantity should he visually checked in all fuel tanks before entering the aircraft.

2. After using the under-seat quick drain, it should be checked from outside the aircraft to make sure it has closed completely, and is not leaking.

3 . Take-off should be made on the fullest main t a n k t o assure best fuel flow, and this tank selected before or immediately after starting in order to allow fuel flow to be adequately established before take-off. The main or tip tank with the highest quantity of fuel should be selected for landing.

4. Fuel tank selection at low altitude is not recommended, since little recovery time is available in the event of an error in tank selection. When switching tanks, make sure that the selector drops into a detent, and i s lined up with the desired tank.

5. The electric fuel pump should be turned on before switching tanks, and should be left on for a short period thereafter.

6- To preclude making a hasty selection, and to provide continuity of flow, it i s desired that the selector be changed to another tank before fuel i s exhausted from the tank in u s e .

7. Operation of the engine driven fuel pump should be checked while taxiing or during pre-take-off engine run-up by switching off the electric fuel pump and observing fuel pressure.

8. During cruise, the electric fuel pump should be in the off position so that any malfunction of the engine driven fuel pump i s immediately apparent.

9. If signs of fuel starvation should occur at any time during flight, fuel exhaustion should be suspected, at which time the fuel selector should be immediately positioned to a full tank and the electric fuel pump switched to the on position.

680220 22

SECTION IV

PERFORMANCE CHARTS

Take-Off Distance vs Density Altitude. 23 &. 24

Rate of Climb vs Density Altitude . - .

• «.

True Airspeed and RPM vs Density Altitude

Range vs Density Altitude

26 & 27

Power vs Altitude . . .

Landing Distance vs Density Altitude .

. . 29

30 Altitude Conversion Chart .

.

Power Setting Tables

. . 31

32 & 33

CHEROKEE 235 " B " SECTION IV

PIPER CHEROKEE

PA-28-235

—i 1 1 r 1 r r ~

TAKEOFF DISTANCE

VS

DENSITY ALTITUDE

FLAPS UP

SHORT FiELD EFFORT

7 0 0 0

6000

5 0 0 0

4 0 0 0

3000 -

2 0 0 0 —

1000

0 500

CONSTANT SPEED PROPELLER

?40C LBS GHOSS WT.

— 2900 LBS- GROSS WT.

63 INCH r|XEO PITCH PROPELLER

2400 LBS GROSS VP\

• 2900 LBS GHOSS WT

UilLZX_L_

1000 1500 2000 !500

TAKEOFF DISTANCE-FEET

680220

SECTION IV CHEROKEE 235 " B "

PIPER CHEROKEE

PA-28-235

7 0 0 0 -

6 0 0 0 i 5 0 0 0

4 0 0 0

3 0 0 0

2 0 0 0

0 0 0

500 1000 1500 2000 2500

TAKEOFF DISTANCE-FEET

PIPER CHEROKEE

Fft-28-235

\ | \

RATE OF CLIMB

VS

DENSITY ALTITUDE "

1 I 1 I

SECTION IV

22000 k

2 0 0 0 0

18000

16000

14000

12000

10000

8 0 0 0

6000

1 f

CONSTANT SPEED PROPELLER

69 INCH FIXED PITCH PROPELLER

\ s

s

\ c i 4

\ v H

\ k

C i

\ vi s \ fc

\ i

1 k:

> s

4 0 0 0

2000

\ \ v

•«.,

x

200 400 600 800 1000 1200 1400

0 f -

RATE OF CLIMB "FEET PER MINUTE

660701

CHEROKEE 235 " B "

SECTION IV

PIPER CHEROKEE

PA-28-235

1

1 1 1

- ' I n u c H i n o r c t . L '

VS

DENSITY ALTITUDE

69 INCH FIXED PITCH PROPELLER

14000

12000 p 10000

- I

>t 8000 en

6000

4000

2000

/ /

r /

10 120 30

2400 LB. GROSS WT

9 Q n n i n ^ R O C Q W T

\ v.

1

\ ,

/ i

. j - i .

/ /

FULL THROTTLE

^ i

>V

\ *

/ /

\i

A f

§1

' \

\ |

Wl'f fit

t u i / /

\ ft6

J a

?//

/ / y\ v

J/ f/ i

! \

/ /

/i A

140 150 160 70

TRUE AIRSPEED MPH

CHEROKEE 235 " B " SECTION IV

PIPER CHEROKEE

PA-28-235

TRUE AIRSPEED

VS

DENSITY ALTITUDE

CONSTANT SPEED PROPELLER

2400 LB. GROSS WT

—2900 LB. GROSS WT

14000

12000

10000

8000

6000

4000

2000

IIO 120 130 140 ISO 160 170

TRUE AIRSPEED, MPH

660701

CHEROKEE 235 " B " SECTION IV

PIPER CHEROKEE

PA-28-235

1 RANGE

VS

DENSITY ALTITUDE

2 9 0 0 LB. MAX.GROSS TAKEOFF WEIGHT

84 GAL. FUEL-FULL TANKS

ECONOMY CRUISE

I ,

U l

, 12000

10000

5 5 % POWER, 129 HP, 10-3GPH

[ i -; | ' i i

65% POWER. 153 HP, H.5GPH

> i i i t i V

I 8 0 0 0

6000 .

7 5 % POWER,

r

'5 HP. 14GPH i ' '-

I i

4 0 0 0

, / /

/ /

I 1 /

/ ' /

2 0 0 0

0 i

800 900 1000 J100 1200

RANGE-STATUTE MILES

CHEROKEE 235 " B "

PIPER CHEROKEE

PA-28-235

POWER

VS

ALTITUDE

LLE R

2900 LB. GROSS WEIGHT

14000

12000 u 10000 —

8000

6000

O 4000

2000 ft

,<t

• #

$rJ

& t

T f

2100 2200 2300 2400 2500 2600

ENGINE SPEED . RPM

SECTION IV

660701 29

SECTION IV CHEROKEE 235 " B '

PIPER CHEROKEE

PA-28-235

6 0 0 0

5 0 0 0

4 0 0 0

3000

2 0 0 0

1000

1

- I 1

1

\ L

' f

' I

1

-i

1 a:/

- ™r

V r

LANDING DISTANCE

vs

DENSITY ALTITUDE

- 2 4 0 0 LB. GROSS WT.

9Qnn i R miasa WT

I i

' f i

/ i

H -

• - i-

1

. O/

8

i o

I f-7

LANDING DISTANCE "FEET

1

660701

CHEROKEE 235 " B I -

PIPER CHEROKEE

PA-28-235

1 I

ALTITUDE CONVERSION CHART

•

THIS CHART SHOULD BE USED TO

DETERMINE (STANDARD! DENSITY

ALTITUDE FROM EXISTING TEMPERATURE

AND PRESSURE ALTITUDE CONDITIONS

FOR USE WITH PERFORMANCE CHARTS

SECTION IV

660701

- 2 0 20 40 60

TEMPERATURE,°F

100

CO oo o to to

Power Setting Table - Lycoming 0-540-8 Engine - Constant Speed Propeller

Press.

Alt

1000

Feet

Std

Alt

Temp

129 HP - 55?= Rated

RPM AND MAN. PRESS.

2100 2200 2300 2400

153 HP -65"o Rated

RPM AND MAN. PRESS.

2100 2200 2300 2400

176 HP - 75*0 Rated

RPM AND MAN. PRESS.

2100 2200 2300 2400

Press

Alt

1000

Feet

20.6

20.3

20.1

19.8

19.6

19.3

19.1

18.8

18.6

18.4

18.2

18.0

17.8

—

20 1

19.8

19 6

19.3

19.1

18 S

18.6

18.3

18 1

17.9

17.7

17.5

17.3

17.1

—

17.6

17 4

17 2

17.0

16.8

16 6

16.4

19.6

19.3

19 1

18.8

18.6

18.3

18.1

17.8

19.2

18.9

18.7

18.4

18.2

17 9

177

17 4

17 2

17 0

16 8

16 6

16 4

16 2

16 1

IS 9

23.2

22.9

22.7

22 4

22 2

21.9

21.7

21.4

21.2

—

22.6

22.3

22,1

21.8

21.6

21.3

21.1

20.8

2 0 6

20.4

—

22.0

21.7

21.5

21.2

21.0

20.7

20.5

20.2

20 0

19.8

19.6

21.5

21.2

21.0

20.7

20.5

20.2

19.9

19.7

19.4

19.2

19.0

25.7 25 0 24 4 23.7

25.4 24.7 24.1 23.4

25.2 24.5 23.8 23.1

24 9 24.2 23.5 22.8

24 7 24 0 23.3

— — -

22.5

22.3

22.0

21.6

To maintain constant power, correct manifold pressure approximately 0 . 1 8 " Hg for each 1CFF variation in carburetor air temperature from standard altitude temperature. Add manifold pressure tor air temperatures above standard; subtract for temperatures be!ow standard. 2 3 0 C26

00 o

Power Setting Table - Lycoming 0-540-B Engine -Fixed Pitch Propeller

• , - - ^ - — . . .

~ , T 1

Press.

Alt

Std Alt

Temp

° F

129 HP

55% Power

RPM

153 HP

65% Power

RPM

176 HP

75% Power

RPM

Press.

Alt

1,000

2,000

3.000

4,000

5,000

6,000

7,000

8,000

9,000

10,000

11.000

12,000

13,000

- . . . • • • • — • .

2170

2190

2210

2230

2250

2270

2285

2305

2320

2340

2360

2380

2400

2420 i 1 — . - • - • — —

2270

2295

2320

2350

2375

2400

2425

2450

2475

2500

2360

2390

2420

2450

2480

2510

2540

2570

1,000

2,000

3,000

4,000

5,000

6,000

7,000

8,000

9,000

10,000

11,000

12,000

13,000

SECTION V

GENERAL MAINTENANCE

Landing Gear Service 34

Brake Service 35

Tire Inflation 35

Care of Windshield and Windows 36

Battery Service 36

Fuel and Oil Requirements 37

Care of Air Filter 37

Leveling and Rigging 37

Serial Number Plate 39

CHEROKEE 235 " B " SECTION V

SECTION V

GENERAL MAINTENANCE

LANDING GEAR SERVICE

Main wheels are easily removed by taking off the hub cap, axle nut, and the two bolts holding the brake segment in place, after which the wheel slips easily from the axle.

Tires are removed from the wheels by first deflating the tire, removing the through b o l t s , and separating the wheel halves.

Landing gear oleo struts should be checked for proper strut exposures and fluid l e a k s . The required extensions for the strut when under normal static load (empty weight of airplane plus full fuel and oil) is 3-1/4 inches for the nose gear and 4-1/2 inches for the main gear. Should the strut exposure be below that required, it should be determined whether air or oil is required by first raising the airplane on jacks. Depress the valve core to allow air to e s c a p e from the strut housing chamber. Remove the filler plug and slowly raise the strut to full compression. If the strut has sufficient fluid it will be visible up to the bottom of the filler plug hole and will then only require proper inflation.

Should fluid be below the bottom of the filler plug hole, oil should be added. Replace the plug with valve core removed, attach a .clear plastic hose t o the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid

(MIL-H-5606). Fully compress and extend the strut several times thus drawing fluid from the container and expelling air from the strut chamber. To allow fluid to enter the bottom chamber of the main gear strut housing, the torque link assembly must be d i s connected to let t h e strut be extended a minimum of 10 inches.

(The nose gear torque links need not be disconnected.) Do not allow the strut to extend more than 12 inches. When air bubbles

680220 34

SECTION V CHEROKEE 235 " B " cease to flow through the h o s e , compress the strut fully and again check fluid level. R e i n s t a l l the valve core and filler plug, and the main gear torque links, if disconnected.

With fluid in the strut housing at the correct level, attach a strut pump, to the air valve and with the airplane on the ground, inflate the oleo strut to the correct height.

In jacking the Cherokee for landing gear service, a jack kit

(available through the Piper Dealers and Distributors) should be used. This kit c o n s i s t s of two hydraulic jacks and a tail stand.

At least 350 pounds of ballast should be placed on the tail stand before jacking the aircraft. The jacks should be placed under the jack points on the wing and the airplane jacked up until the tail skid is at the right height to attach the tail stand. After attaching the tail stand and adding ballast, jacking may be continued until the aircraft i s at the height desired.

BRAKE SERVICE

The brake system is filled with MIL-H-5606 (petroleum b a s e ) hydraulic brake fluid. This should be checked at every 100 hour inspection and replenished when necessary by filling the brake reservoir on the firewall to the indicated level. If the system a s a whole has to be refilled, it should be done by filling with fluid under pressure from the brake end of the system. This will eliminate air from the system.

No adjustment of brake clearances is necessary on the Cherokee. If after extended service the brake blocks become worn excessively, they are easily replaced with new segments.

TIRE INFLATION

For maximum service from the Cherokee tires, keep the tires inflated to a pressure of 35 to 40 pounds for the main gear and 28 to 30 pounds for the nose gear. If necessary, interchange the tires on the main wheels to produce even wear. All wheels and

35 680220

CHEROKEE 235 " B " SECTION V tires are balanced before original installation, and the relationship of the tire, tube and wheel should be maintained if possible.

Out of balance wheels can cause extreme vibration on take-off.

In the installation of new components, it may be necessary to rebalance the wheel with the tires mounted.

CARE OF WINDSHIELD AND WINDOWS

A certain amount of care i s needed t o keep the plexiglas windows clean and unmarred. The following procedure i s recommended:

1. Flush with clean water and dislodge excess dirt, mud, etc., with your hand.

2. Wash with mild soap and water. Use a soft cloth or sponge, do not rub.

3. Remove oil, grease or sealing compounds with a soft cloth and kerosene.

4. After cleaning, apply a thin coat of hard polishing wax.

Rub lightly with a soft cloth,

5. A severe scratch or mar may be removed by using jeweler's rouge to rub out the scratch, smoothing, and then applying wax.

6. If it i s found that fog, stains, e t c . , appears on the inner surfaces of the double window assemblies, refer to the Cherokee

Service Manual for cleaning instructions.

BATTERY SERVICE

Access to the 12 volt battery is through the right rear baggage compartment panel. The s t a i n l e s s steel box has a plastic drain tube which i s normally closed off with a clamp and which should be opened occasionally to drain off any accumulation of liquid. The battery should be checked for proper fluid level but must not be filled above the baffle plates. A hydrometer check should be performed to determine the percent of charge present

680220

SECTION V CHEROKEE 235 " B "

in the battery.

If the battery is not up to charge, recharge starting at a 4 amp rate and finishing with a 2 amp rate. Quick charges are not recommended.

FUEL AND OIL REQUIREMENTS

Aviation grade 80/87 Octane (minimum) fuel must be used in the Cherokee. The use of lower grades can cause serious engine damage in a very short period of time, and is considered of such importance that the engine warranty is invalidated by such use.

The oil capacity of the Lycoming O-540 series engines is 12 quarts and the minimum safe quantity is 2-3/4 quarts. It is recommended that engine oil and oil filter element be changed every

50 hours or sooner under unfavorable conditions. The following grades are recommended for the specified temperatures:

Temperatures above 60° F SJV.E. 50

Temperatures between 30°F and 90° F S.A.E. 40

Temperatures between 0° F and 70° F S.A.E. 30

Temperatures below 10* F S.A.E- 20

CARE OF AIR FILTER

The carburetor air filter must be cleaned at least once every fifty hours. Under extremely adverse conditions of operation it may be necessary to clean the filter daily. Extra filters are inexpensive and a spare should be kept on hand and used as a rapid replacement.

The filter manufacturer recommends that the filter be tapped gently to remove dirt particles. Do not blow out with compressed air.

37 680220

CHEROKEE 235 " B " SECTION V

LEVELING AND RIGGING

Leveling the Cherokee for purposes of weighing or rigging i s accomplished a s follows:

1. Partially withdraw two machine screws located immediately below the left front side window. T h e s e screws are leveling points and the airplane is longitudinally level when a level placed on the heads of these screws indicates level.

2. To put the airplane in a longitudinally level position on s c a l e s , first block the main gear oleos in the fully extended position, then deflate the nose wheel tire until the proper attitude is obtained. For rigging only, the airplane may be placed on j a c k s for leveling.

3. To level the airplane laterally, place a level across the baggage compartment floor along the rear bulkhead.

Rigging: Although the fixed flight surfaces on the Cherokee cannot be adjusted for rigging purposes, it may be necessary upon occasion to check the position of these surfaces. The movable surfaces all have adjustable s t o p s , as well as adjustable turnbuckles on the cables or push-pull tubes, so that their range of travel can be altered. The positions and angular travels of the various surfaces are as follows;

1. Wings: 7° dihedral, 2° washout.

2. Stabilator Travel: 18° up, 2° down, tolerance + / - 1

3. Fin should be vertical, and i n l i n e with center of fuselage.

4. Ailerons Travel: 30° up, 15° down, tolerance +/-2

5. Flaps Travel: 10°, 25°, 40°, tolerance +/"2°.

6. Rudder Travel: 27° right and left, tolerance l / - 2

7. Stabilator Tab Travel: 3° up, 12 c

down, tolerance + / - 1 ° .

Cable tensions for the various controls are a s follows:

Rudder: 40+/-5# Stabilator: 4CH-/-5#

Ailerons: 40+_/-5£ Stabilator Trim: 5 t / - l #

680220 38

SECTION V CHEROKEE 235 " B "

SERIAL NUMBER PLATE

The serial number plate is located near the stabilator on the left side of the airplane. Refer to this number for service or warranty matters.

680220

FUEL QUANTITY GAUGES pjfaia' yyff . "Snrjrj rXiv^-

RIGHT TIP TANK

FUEL SELECTOR CONTROL

FUEL SYSTEM

«ZJ

CHEROKEE 235 " B "

HOURS

RUDDER HINGES ICO

AtfD HORN

STABILATOR IOQ

HIHGES

STABILATOR TRIM

TAB

STABILATOR

ADJUSTMENT

MECHANISM

STABILATOR

CONTROL

PULLEYS

BAGGAGE DOOR

AND MAIN DOOR

HINGES

A1LERON AND F L A P

TORQUE TUBE,

PULLEYS,

BELLCRANK,

LEFT AND RIGHT

AILERON HINGES 50

MAIN LANDING GEAR

TORQUE LINKS

MAIN WHEEL

BEARINGS

LEFT AND RIGHT

HATES

1. OLEC STRUTS AND BRAKE RESERVOIR _ F I L L PER INSTRUCTIONS ON UNIT

OR CONTAINER, OR REFER TO SERVICE MANUAL, SECTION I I .

2. INTERVALS BETWEEN OIL CHANGES CAN BE INCREASED AS MUCH AS 103%

ON ENGINES EQUIPPED WITH F U L L FLOW (CARTRIDGE TYPE) OIL FILTERS -

PROVIDED THE ELEMENT IS REPLACED EACH SO HOURS OF OPERATION.

3. PROPELLER - R E M O V E ONE OF THE TWO GREASE FITTINGS FOR EACH BLADE

APPLY GREASE THROUGH FITTING UNTIL FRESH GREASE APPEARS AT HOLE

OF REMOVED F I T T I N G .

4. INDUCTION FILTER - CLEAN PAPER AIR F I L T E R BY TAPPING THE UNIT

LIGHTLY AGAINST A HARD SURFACE. DC NOT USE SOLVENT OR COMPRESSED

AIR. REPLACE WHEN NECESSARY.

5. FUEL SELECTOR V A L V E - LUBRICATE AREA WHERE DETENT B A L L MOVES

ACROSS COVER P L A T E WITH DUPONT A L L PURPOSE SLIP SPRAY P6611 OR

EQUIVALENT.

•

ENGINE

LEGEND

MIL-L-7870 OIL - GENERAL PURPOSE

LOW TEMP, LUBRICATION.

MlL-C-23827 GREASE - LUBRICATION

GENERAL PURPOSE AIRCRAFT

MIL-L-3S4S GREASE - LUBRICATION

HIGH TEMP.

M1L-H-S6M HYDRAULIC FLUID (RED).

SAE 50 ABOVE 4 f l

F AIR TEMP. '

SAE40 30-F T 0 90-F AIR TEMP. '

SAE 30 0- F TO 70- F A I R TEMP. '

SAE 20 BELOW 10-F AIR TEMP- *

680220

SECTION V

HOURS

STABILATOR TRIM

250 PULLEYS

(SEE CAUTION 4)

pm mmmm PA-SS-

•

*6ME

LEGEHO

MIL-L-7870 OIL - GENERAL PURPOSE

LOW TEMP, LUBRICATION.

MIL-G-23827 GREASE - LUBRICATION

GENERAL PURPOSE AIRCRAFT-

MIL-L-3S4S GREASE - LUBRICATION

HIGH TEMP.

M1L-H-S6O6 HYDRAULIC FLUID (RED).

SAE 50 ABOVE 40--F AIR TEMP. '

SAE 40 30-F TO 90*F AIR TEMP. '

SAE 30 0- F TO 70- F A I R TEMP. '

SAE 20 BELOW 10'F AIR TEMP-"

100 CONTROL COLUMN

BRAKE RESERVOIR

MAINTAIN FLUID s 0

LEVEL INDICATED

ON THE SIDE OF

RESERVOIR

RUDDER ADJUSTMENT

TOO MECHANISM AND

RUDDER ASSEMBLY

PROPELLER GREASE

100 FITTINGS {CONSTANT

SPEED) inn FRONT SEAT

ADJUSTMENT

100

NOSE WHEEL

STEERING inn NOSE WHEEL

, U U

BEARINGS

NOSE LANDING GEAR

TORQUE LINKS

ENGINE OIL

50 DRAIN AND REFILL

12 U.S. QTS.

100

FUEL SELECTOR VALVE

SEE NOTE S

CAUTIONS

1. DO NDT USE A HYORAULIC FLUID WITH A CASTOR OIL OR ESTER

BASE.

2- DO NOT OVER-LUBRICATE PEDESTAL CONTROLS.

3. DO NOT APPLY LUBRICANT TO RUBBER PARTS.

4. UNDER NO CIRCUMSTANCES SHOULD THE TRIM CABLES FROM THE

COCKPIT TO THE REAR OF THE FUSELAGE BE LUBRICATED - AS

THIS MAY CAUSE SLIPPAGE.

5- REMOVE ALL EXCESS GREASE FROM GREASE FITTINGS.

4. OIL AILERON HINGES EVERY FIFTY HOURS

• NON-DETERGENT. SEE LYCOMING SERVICE INSTRUCTIONS

NO- 1014 FOR USE OF DETERGENT OIL.

41/42

CHEROKEE 235

680220

F I B - TANK SENDERS

8-Co.

it

5 ^

Sim ttU.i C |

0 * ^

-I LI 2

SECTION V

FU£L

PUWP

tmwt-xff^gh

NOTES:

I . UTB-UPPER TERMINAL 8L0CK

2 . LTB - LOWER TERMINAL BLOCK

ELECTRICAL SCHEMATIC

43/44

INDEX

SECTION I Page

Specifications; 1

Performance 1

Weights 2 .

Power Plant 2

Fuel and Oil , 3

Baggage 3

Dimensions 3

Landing Gear 3

SECTION II

Design Information: . 5

Engine and Propeller 5

Structures. 6

Landing Gear .

. 7

Control System .

. 7

Fuel System , 8

Electrical System .

. 9

Heating and Ventilating System .

. 10

Cabin Features 13

SECTION Ml

Operating Instructions: . 14

Preflight 14

Starting Engine 15

Warm-Up 16

Ground Check 17

Take-Off 18

Climb • 18

Stalls 19

Cruising 19

Approach and Landing 20

Mooring 21

Weight and Balance 21

Fuel System Operating Procedures .

. 22

680220

INDEX (cont)

SECTION IV

Performance Charts:

• •

Take-Off Distance vs Density Altitude

Rate of Climb v s Density Altitude . .

True Airspeed and RPM vs Density Altitude

Range vs Density Altitude

Power vs Altitude .

Landing Distance vs Density Altitude , ,

Altitude Conversion Chart .

Power Setting Tables .

Page

•

23 & 24

* 25

26 & 27

- 28

. 29

. 31

32 &33

SECTION V

General Maintenance:

Landing Gear Service .

. 34

Brake Service 35

Tire Inflation 35

Care of Windshield and Windows. .

. 36

Battery Service .

Fuel and Oil Requirements

Care of Air Filter 37

Leveling and Rigging 37

Serial Number Plate 39

680220

Hello! I am an AI chatbot specifically trained to assist you with the Piper Cherokee 235 'B' Airplane Owner's Handbook. I have thoroughly reviewed the document and can help you locate the exact information you need or explain the content in clear and simple terms. Whether you’re looking for guidance on specific features, troubleshooting steps, or general usage, feel free to ask your questions. The more details you provide about your concerns or needs, the more accurately and effectively I can assist you!

Show related prompts

Assistant typing

Assistant terminated

Key features

Single-engine
Four-seat
High-wing
235 horsepower engine
84 gallons fuel capacity
200 pounds baggage weight
Good handling
Good performance

Frequently asked questions

The engine is rated at 235 horsepower at 2575 rpm.

The standard fuel capacity is 84 gallons.

The maximum baggage weight is 200 pounds.

The engine requires 80/87 minimum octane aviation fuel.

The propeller used on the PA-28-235 is either the McCauley 1P235PFA80 fixed pitch aluminum alloy unit or the Hartzell HC-C2YK-1/8468A-4 constant speed propeller.