Piper CHEROKEE CRUISER PA-28-140 Information Manual

Below you will find brief product information for Piper CHEROKEE CRUISER PA-28-140. This manual is intended to help you with operating your aircraft safely and efficiently. It provides information on the aircraft's systems, performance, and limitations. By understanding and following the information in this manual, you can increase your enjoyment and safety while flying your aircraft.

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THE

PILOT’S OPERATING MANUAL

REFERENCE ONLY

THIS ELECTRONIC VERSION

OF THE POM/AFM IS

NOT APPROVED TO

REPLACE ANY OPERATING

INFORMATION REQUIRED

BY THE REGULATIONS.

BY

This manual is incomplete without an APPROPRIATE FAA APPROVED AIRPLANE

FLIGHT MANUAL and an APPROPRIATE WEIGHT AND BALANCE REPORT.

WARNING

EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL

TO APPLICABLE AIRCRAFT. THIS MANUAL REVISED AS INDICATED BELOW

OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE

IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION.

SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION

MUST BE PROPERLY INSERTED.

MODEL PA-28-140

PIPER AIRCRAFT CORPORATION

APPROVALSIGNATUREANDSTAMP _________________________ __ ii

Assurance that the airplane is in an airworthy condition is the responsibility of the owner.

The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining within the operating limitations outlined by the Airplane Flight

Manual, instrument markings, and placards.

This Pilot's Operating Manual is not designed as a substitute for adequate and competent flight instruction, knowledge of the current airworthiness directives, applicable federal air regulations, or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual for transition from single to multi-engine flying.

If an inconsistency of information exists between the Pilot's Operating Manual and the

Airplane Flight Manual approved by the F AA, ~he Airplane Flight Manual shall be the authority.

A complete or partial replacement of this manual, Part No.

761 555, may be obtained only from Piper Customer Services.

Published by

PUBLICATIONS DEPARTMENT

Piper Aircraft Corporation

761 555

Issued : July 1973

APPLICABILITY

This manual is applicable to Piper Model PA-28-140 aircraft having serial numbers

28-7425001 through 28-7625275. Contact Piper Customer Services for specific information on the application of this manual.

REVISIONS

The 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 to 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.

II. 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. Original Pages Issued

The original pages issued for this manual prior to revision are given below:

1-1 through 1-4, 2-1 through 2-18, 3-1 through 3-18, 4-1 through 4-6, 5-1 through 5-32,

7-1 through 7-11,8-1 through 8-2, 9-1 through 9-11,10-1 through 10-15. iii

Rev. I - 761 555

(PR731022)

PILOT'S OPERATING MANUAL LOG OF REVISIONS

Current Revisions to the PA-28-l40 Cherokee Cruiser Pilot's Operating Manual, 761 555, issued

July 6, 1973.

Revision

Revised

Pages

Description Date

1-1

Rev. 2 - 761 555

(PR740529)

W/B

9-4

9-5

9-6

9-7

11 iii

AF/M

W/B

Changed Instructional Power Cruise Speed Oct. 22, 1973 from 50% to 60%.

Added Rev. 1 to Report: VB-546.

Added "Best Economy Mixture".

Revised type size.

Removed NOTE.

Added PAC Approval Form.

Added Applicability and Item III. Original

Pages Issued.

Added Rev. [ to Report: VB-557.

Added Rev. 2 to Report: VB-546.

(NOTE: AIRCRAFT DELIVERED WITH

MANUALS PRIOR TO THIS REVISION

DO NOT REQUIRE THIS REVISION.)

May 29, 1974

Rev. 3 - 761 555

(PR740613)

Title

2-1

2-2

2-8

2-9

2-9a

2-10

2-11

2-12

2-12a

AF/M

4-6

W/B

7-i

7-4

7-5

7-6

Added Flite Liner.

Added reference to Flite Liner to The

Airplane; relocate info to page 2-2.

Added info from page 2-1 .

Added annunciator panel info and foot note; relocated info to page 2-11.

Revised Alternator and Starter Schematic.

Added page (Alternator and Starter

Schematic).

Relocated page.

Relocated page; added info from page 2-8; added annunciator panel to Vacuum System and Instrument Panel; added footnote.

Relocated page; added annunciator panel.

Added page.

Added Rev. 2 to Report: VB-557.

Revised Alternator Failure, item 3.

Added Rev. 3 to Report: VB-546.

Added Airspeed Data and revised page nos.

Added annunciator panel and footnote.

Revised Stall info; deleted stall table; added Cruising info from page 7-6; revised

Cruising info; revised stall info.

Relocate Cruising to page 7-5; added

Approach-and Landing info from page 7-7.

June 13,1974 iv

Revision

Rev. 3 (cont)

Rev. 4 - 761 555

(PR7411Ol)

Rev. 6 - 761 555

(PR750516

Rev. 7 - 761 555

(PR750718)

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)

Rev. 5 - 761 555

(PR750121)

Revised

Pages

7-7

Description Date

8-1

8-2

9-i

9-2

9-3

9-4

9-5

9-6

9-7

9-8

9-9

9-10

9-11

1-2

AF/M

W/B

7-4

8-2

2-16

W/B

7-10

7-11

Added Airspeed Data; relocated Approach and Landing info to page 7-6.

Revised item 6. (added annunciator); added footnote; relocated info from item 8. to page 8-2.

Added info from page 8-1.

Revised chart nomenclature.

Revised Takeoff chart.

Revised Climb chart.

Revised Power chart.

Revised Cruise chart.

Revised Range chart (36 gal).

Revised Range chart (50 gal).

Revised Glide chart.

Revised Stall chart (weight).

Revised Stall chart (angle of bank).

Revised Landing chart.

Revised footnote.

Added Rev. 3 to Report: VB-557.

Added Rev. 4 to Report: VB-546.

Added new item 9. and revised existing item nos. under Takeoff.

Added item 11.

Nov. 1,1974

Revised Stall Warning description.

Added Rev. 5 to Report: VB-546.

Revised Operating Instructions for Emergency

Locator Transmitter; relocated material to page 7-1l.

Added material relocated from page 7-10.

Jan. 21, 1975

May 16, 1975 1-2

W/B

8-1

8-2

2-1

2-10

2-12

W/B

Revised Empty Weight and Useful Load.

Added Rev. 6 to Report: VB-546.

Relocated item 8. (fuel tip) to page 8-2.

Added and revised item 8. (fuel tip).

Deleted info (AIRFRAME).

Added callout.

Added Engine Hour Meter; revised callouts.

Added Rev. 7 to Report: VB-546.

July 18, 1975 iv-a

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)

Revision

Rev. 8 - 761 555

(PR751127)

Rev. 9 - 761 555

(PR760419)

Rev. 10 - 761 555

(PR760719)

Rev. 11 - 761 555

(PR770603)

Rev. 12 - 761 555

(PR770930)

10-10

10- 11

10-12

10-13

10-14

W/B

7-10

7-11

Revised

Pages

AF/M

WIB

7-11

8-2

1-2

AF/M

7-4

7-5

7-6

8-2 lO-i

10-8

10-9

7-2

7-11

...

III

AF/M

W/B

Description

Added Rev. 4 to Report: VB-557.

Added Rev. 8 to Report: VB-546.

Revised ELT info.

Revised item 8.

Revised Fuel Specifications.

Added Rev. 5 to Report: VB-557.

Added Note.

Revised Cruising Info.

Revised Approach and Landing item 2.

Added items 12, 13, 14.

Revised page nos. for Filling Fuel Tanks,

Draining Fuel Valves and Lines, Facts You

Should Know, and Required Service and

Inspection Periods.

Revised Fuel Requirements; relocated

Filling Fuel Tanks to page 10-9.

Added Fuel Grade Comparison Chart and info from page 10-8; relocated Draining

Fuel Valves and Lines to page 10-10.

Added info from page 10-9 and relocated

Facts You Should Know to page 10-11.

Added info from page 10-10 and relocated info to page 10-12.

Added info from page 10-11 and relocated info to page 10-13.

Added info from page 10-12.

Revised Special Instruction No.7.

Added Rev. 9 to Report: VB-546.

Added info from page 7-11. Deleted info about Emergency Locator Transmitter.

Moved info to page 7-10; revised pilot's remote switch description.

Revised Starting Engines When Hot.

Revised ELT Note.

Added Applicable Serial Numbers.

Added Rev. 6 to Report: VB-557.

Added Rev. 10 to Report: VB-546.

(NOTE: AIRCRAFT DELIVERED WITH

MANUALS PRIOR TO THIS REVISION

DO NOT REQUIRE THIS REVISION.)

Date

Nov. 27, 1975

April 19, 1976

July 19, 1976

June 3,1977

Sept. 30, 1977 iv-b

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)

Revision

Rev. 13 - 761 555

(PR790416)

Rev. 14 - 761 555

(PR800522)

Rev. 15 - 761 555

(PR840713)

Rev. 16 - 761 555

(PR900316) iv-c

10-8

10-8a

10-8b

10-9

10-11

10-13 l-i

1-2

1-3

2-6

AF/M

W/B

7-1

7-4,

8-1

9-i

10-8

10-11

10-12

10-13

Revised

Pages

2-8

2-14

W/B

7-10

10-10

10-11

2-8

W/B

Description

Added Warning.

Added Caution.

Added Rev. 11 to Report: VB-546.

Revised ELT info.

Added Caution; relocated info. to pg. 10-11.

Added info. from pg. 10-10.

Revised Warning.

Added Rev.12 to Report: VB-546.

Date

April 16, 1979

May 22,1980

Revised General Specifications.

Relocated Dimensions to pg. 1-3: revised fuel and Oil specification.

Added Dimensions from pg. 1-2.

Revised fuel info.

Added Rev. 7 to Report: VB-557.

Added Rev. 13 to Report: VB-546.

Revised Preflight.

Added ending serial number effectivity.

Added Warning.

Revised Fuel Requirements.

Revised Handling and Servicing (Facts

You Should Know).

Revised Preventive Maintenance.

Deleted Preventive Maintenance info.; revised Required Service and Inspection

Periods.

July 13, 1984

Added Rev. 16 to 761 555 Log of Revisions. March 16, 1990

Revised Oil Requirements. Moved Fuel

System to page 10-8a.

Added page. Revised and moved Fuel System from page 10-8.

Added page.

Revised Fuel Grade Comparison Chart.

Revised Handling and Servicing (Facts

You Should Know).

Revised Required Service and Inspection

Periods. iv-c

GENERAL SPECIFICATIONS

DESCRIPTION - AIRPLANE AND SYSTEMS

AIRPLANE FLIGHT MANUAL F.A.A. APPROVED

EMERGENCY PROCEDURES F.A.A. APPROVED

EMERGENCY PROCEDURES

WEIGHT AND BALANCE

LOADING INSTRUCTIONS

OPERATING INSTRUCTIONS

OPERATING TIPS

PERFORMANCE CHARTS

HANDLING AND SERVICING

GENERAL SPECIFICATIONS

Performance .... .... ........... ...... ........ ...... ... ... ... .... ............ ..... ......... .... ....... ... ..... ............ ...... .................. I-I

Weights ............................................................................................................................................. 1-2

Power Plant ...................................................................................................................................... 1-2

Fuel................................................................................................................................................... 1-2

Oil .................................................................................................................................................... 1-2

Baggage ............................................................................................................................................ 1-2

Dimensions ................................ .................... .................................................................................. 1-3

Landing Gear .............................. .................................................................................. .................... 1-3 l-i

CHEROKEE CRUISER

GENERAL SPECIFICATIONS

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 installed, the condition of engine, airplane and equipment, atmospheric conditions and piloting technique. Each performance figure below is subject to the same conditions as on the corresponding performance chart from which it is taken in the Performance Charts Section.

Takeoff Ground Run, flaps up, sea level (ft)

Takeoff Distance Over 50-ft Obstacle, flaps up, 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 Alt, 7800 ft, 75% power (TAS) (mph)

Service Ceiling (ft)

Absolute Ceiling (ft)

Cruise Speed at best power mixture, optimum altitude (TAS) (mph)

65% power, 10,250 ft

55% power, 11,900 ft

Range at best power mixture optimum altitude (mi)**

75% power, 7,800 ft

65% power, 10,250 ft

55% power, 11,900 ft

Cruise Speed at best economy mixture, optimum altitude (mph)

75% power, 7,000 ft

65% power, 10,000 ft

55% power, I 2,000 ft

Range at best economy mixture, optimum altitude (mi)**

75% power, 7,000 ft

65% power, 10,000 ft

55% power, 12,000 ft

Cruising Speed, sea level, 75% power (mph)

Instructional power cruise speed, sea level, 60% power (mph)

Cruising range, sea level, 75% power (mi)

Instructional power cruising range, sea level, 6090 power, (mi)

720

795

880

124

110

475

(675***)

540

(760***)

705

765

855

126

120

114

800

1700

631

142*

135*

10,950

13,000

127

114

* All speeds stated are with optional wheel fairings installed. Subtract 3 mph if wheel fairings are not installed.

** Ranges based on 48 gal usable fuel, no reserve.

***Ranges adjusted to reflect the use of best economy speeds with best economy fuel flows, and 48 gallons usable.

GENERAL SPECIFICATIONS

REVISED: OCTOBER 22, 1973 1-1

CHEROKEE CRUISER

Fuel Consumption, 75% power (gal per hr)

Fuel Consumption, 50% power (gal per hr)

Stalling Speed, flaps down (mph)

Landing Roll, flaps down (ft)

WEIGHTS

Gross Weight (Ibs)

Standard Empty Weight (Ibs)

Maximum Useful Load (Ibs)

POWER PLANT

Engine - Lycoming

Rated Horsepower and Speed (rpm)

Bore (inches)

Stroke (inches)

Displacement (cubic inches)

Compression Ratio

Dry Weight (pounds)

Oil Sump Capacity (quarts)

Propeller (Sensenich)

FUEL

AVGAS ONLY

Fuel Capacity (U.S. gal) Standard

Fuel Capacity (U.S. gal) Reserve

Fuel, Aviation Grade

Minimum Octane

Specified Octane

Alternate Fuels

OIL

Oil Capacity (quarts)

BAGGAGE

Maximum Baggage (Ibs)

Baggage Space (cubic ft)

8.4

5.6

535

2150

1275

875

0-320-E3D

150 at 2700

5.125

3.875

319.8

7: 1

276

M74DM

80/87

Refer to Fuel Requirements,

Section 10 - Page 10-8

200*

* See Weight and Balance for limitations when family seats and safety family seats are installed or baggage area mofified in accordance with Piper Drawing 66671.

1-2

GENERAL SPECIFICATIONS

REVISED: JULY 13, 1984

DIMENSIONS

Wing Span (ft)

Wing Area (sq ft)

Wing Loading (lbs per sq ft)

Length (ft)

Height (ft)

Power Loading (Ibs per hp)

LANDING GEAR

Wheel Base (ft)

Wheel Tread (ft)

Tire Pressure (Ibs)

Tire Size

Nose

Main

Nose (4 ply rating)

Main (4 ply rating)

CHEROKEE CRUISER

160

13.4

23.3

7.3

14.3

6.2

10.0

6.00 x 6

GENERAL SPECIFICATIONS

REVISED: JULY 13, 1984 1-3

CHEROKEE CRUISER

63.75"--1

1-4

+-----10'---~

~-------23' 5.4" - - - - - /

STATIC GROUND LINE

GENERAL SPECIFICATIONS

ISSUED: JULY 6, 1973

DESCRIPTION

AIRPLANE AND SYSTEMS

The Airplane .................................................................................................................................... 2-1

Airframe........................................................................................................................................... 2-1

Engine and Propeller........................................................................................................................ 2-1

Landing Gear..................................................................... ................. ............................................. 2-2

Flight Controls ................................................................................................................................. 2-5

Fuel System ..................................................................................................................................... 2-5

Electrical Systen1 .................................................................................................... ......................... 2-8

Vacuum System ............................................................................................................................... 2-11

Instrument Panel.. ............ ........... ... ........... ..... ......... ......... ...................... ...... ............ .... ....... ...... ....... 2-11

Pitot-Static System........................................................................................................................... 2-14

Heating and Ventilating System... ....... .... ......... ..... ..... ...... ...... ............ ........ .................. ....... ...... ....... 2-14

Cabin Features ........... ... ............... ........... ......... ..... ..... ......... ... ...... ...................... .......... ....... ...... ....... 2-16

Baggage Area. ................ ......... ..... ... ........ ..... ........ .... ........... ...................... ...... ... ......... ........ ........ ..... 2-16

Stall Warning ................................................................................................................................... 2-16

Finish ............................................................................................................................................... 2-16

Air Conditioning .............................................................................................................................. 2-17

Piper External Power... ....... .......... ............... ..... ......... ...... .............. ........ ........... ...... .......... ..... .......... 2-18

2-i

CHEROKEE CRUISER

DESCRIPTION

AIRPLANE AND SYSTEMS

THE AIRPLANE

The Cherokee 140 is a single-engine, low wing monoplane of all metal construction. It is available in two versions, the Cherokee Cruiser and the Cherokee Flite Liner.

The Cherokee Cruiser, which is the standard model, has a two-place configuration with a third and fourth family seat offered as optional equipment. Economy, comfort and a wide range of options make the Cherokee Cruiser a versatile business or personal airplane.

The Cherokee Flite Liner is basically a standard model Cruiser with optional equipment installed that is tailored for flight instruction. This equipment includes instruments, radio and lights. The Cherokee Flight Liner also has its own distinctive exterior color scheme. The simplicity, stability and dual flight controls make it an especially good instructional airplane.

AIRFRAME

The basic airframe is of aluminum alloy construction. The extremities - wing tips, cowling, tail surfaces - are of durable fiberglass.

The wings are attached to each side of the fuselage by insertion of the butt ends of the respective main spars into a spar box carry-through which is an integral part of the fuselage structure, providing, in effect, a continuous main spar with splices at each side of the fuselage.

There are also fore and aft attachments at the rear spar and at an auxiliary front spar.

The wing airfoil section is a laminar flow type, NACA65

-415 with the maximum thickness about 40% aft of the leading edge. This permits the main spar carry-through structure to be located under the rear seat, providing unobstructed cabin floor space ahead of the rear seat.

ENGINE AND PROPELLER

The Lycoming 0-320-E3D engine installed in the Cherokee PA-28-140 is rated at 150 horsepower at 2700 rpm. This engine has a compression ratio of 7 to I and requires 80/87 minimum octane fuel. The engine is equipped with direct drive or optional geared drive starter, a 60 ampere alternator, dual magnetos, vacuum pump drive, diaphragm type fuel pump and a float carburetor.

Exhaust gases are carried through a system constructed of heavy gauge stainless steel which incorporates heater shrouds to provide cabin heat, defrosting, and carburetor deicing.

AIRPLANE AND SYSTEMS

REVISED: JULY 18, 1975 2-1

CHEROKEE CRUISER

The propeller used on the PA-28-140 is a Sensenich M74DM fixed-pitch aluminum alloy unit. Its diameter is 74 inches with a standard pitch of 58 inches. All performance figures are based on the standard 58 inch pitch propeller.

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 quadrant is in the lower center of the instrument panel and contains the throttle and mixture control. A friction lock on the right side of the quadrant prevents creeping of the controls. To the right of the quadrant is the carburetor heat control that provides maximum carburetor heat when fully ON. Air passes through a highly efficient dry type filter when the carburetor heat is OFF.

The Flite Liner incorporates a throttle detent adjusted to the 60% power location for the throttle control. When the throttle is set in this detent, the tachometer needle will match the white radial decal indicating 2265 RPM on the glass of the tachometer at 3500 feet altitude.

The arcs of this decal represent 60% power at sea level (2180 RPM) and 7000 feet (2345 RPM).

Thus an economical 60% power setting can be easily obtained up to 7000 feet altitude.

LANDING GEAR

The three landing gears use Cleveland 6.00 x 6 wheels, the main wheels are being provided with brake drums and Cleveland single disc hydraulic brake assemblies. The nose wheel and the main gear all use 6.00 x 6 four ply tires with tubes.

The nose gear is steerable through a 60° arc by use of the rudder pedals and brake. 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 bungee device to provide lighter, smoother ground steering and to dampen bumps and shocks during taxiing.

The nose gear also includes a shimmy dampener.

The oleo struts are of the air-oil type with a normal extension of 3.25 inches for the nose gear and 4.50 inches for the main gear under normal static (empty weight of airplane plus full fuel and oil) load.

The brakes are actuated by a hand lever and a master cylinder which is located below and near the center of the instrument panel. The toe brakes and the hand 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 lever and depressing the 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.

2-2

AIRPLANE AND SYSTEMS

REVISED: JUNE 13, 1974

CHEROKEE CRUISER

'1,

I, "

: i!

""-..,""-..

AIRPLANE AND SYSTEMS

ISSUED: JULY 6, 1973

Main Wheel Assembly

2-3

CHEROKEE CRUISER

2-4

Throttle Quadrant and Console

AIRPLANE AND SYSTEMS

ISSUED: JULY 6,1973

CHEROKEE CRUISER

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 acting as a longitudinal trim tab. It is actuated by a control wheel on the floor between the front seats. The stabilator provides extra stability and control with less size, drag, and weight than conventional tail surfaces. The differential action of the ailerons tends to eliminate adverse yaw in timing maneuvers and reduces 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.

FUEL SYSTEM

Fuel is stored in two twenty-five gallon tanks which are secured to the leading edge structure of each wing by screws and nut plates to allow easy removal for service or inspection.

The fuel selector control is located on the left side panel, forward of the pilot's seat. The button on the selector cover must be depressed and held while the handle is moved to the OFF position. The button releases automatically when the handle is moved back into the ON position.

AIRPLANE AND SYSTEMS

ISSUED: JULY 6,1973 2-5

CHEROKEE CRUISER

-~.-

--:-.:. ..

.-::.::-...,--

--:::--:.'

~--

-.--~~

?',;,...;-.

---

':...-

' .

?~-

Fuel Selector

To obtain the standard fuel quantity of 36 gallons, fill the tanks to the bottom of the filler neck indicator. To obtain the standard plus the reserve quantity, a total of 50 U.S. gallons, fill the tanks to the top of the filler neck.

An auxiliary electric fuel pump is provided for use in case of failure of the engine driven pump. The electric pump should be on for all takeoffs and landings and when switching tanks.

The fuel strainer is equipped with a quick drain and is located on the front lower left corner of the fire wall. This strainer should be drained during preflight to check for water or sediment and proper fuel (a special bottle is furnished for this operation). To drain the lines from the tanks, the tank selector valve must be switched to each tank in turn, with the electric pump on, and the gascolator drain valve opened. Each tank has an individual quick drain located at the bottom, inboard, rear corner.

Fuel quantity and pressure are indicated on gauges located in the engine gauge cluster on the left side of the instrument panel.

An engine priming system is installed to facilitate starting. The primer pump is located on the immediate left of the throttle quadrant.

2-6

AIRPLANE AND SYSTEMS

REVISED: JULY 13, 1984

CHEROKEE CRUISER

FUEL QUAHTnl GAUGES

MAIN TANK

FUEL TANK SELECTOR VALVE

FUEL PRESSURE GAUGE

MAIN TANK

ENGINE FUEL PUMP

ELECTRIC FUEL PUMP

CARBURETOR

AIRPLANE AND SYSTEMS

ISSUED: JULY 6,1973

Fuel System Schematic

2-7

CHEROKEE CRUISER

ELECTRICAL SYSTEM

The electrical system includes a 14-volt 60 ampere alternator, battery, voltage regulator, overvoltage relay, and master switch relay. The 12-volt battery and master switch relay are located beneath the baggage compartment floor. Access for service or inspection is obtained by raising the hinged floor panel. The regulator and overvoltage relay are located on the fuselage behind the instrument panel.

Electrical switches are located on the right center instrument panel, and the circuit breakers are located on the lower right instrument panel. A rheostat switch on the right side of the switch panel controls the navigation lights and the intensity of the instrument panel light.

Standard electrical accessories include starter, electric fuel pump, stall warning indicator, cigar lighter, ammeter, and annunciator panel *.

Optional electrical accessories include navigation lights, anti-collision light, landing light, and instrument panel lighting.

The Flite Liner includes as standard electrical accessories: starter, electric fuel pump, stall warning indicator, ammeter, navigation lights, anti-collision light, landing light, instrument panel lights, and annunciator panel*.

WARNING

Anti-collision lights should not be operating when flying through cloud, fog or haze, since the reflected light can produce spatial disorientation. Strobe lights should not be used in close proximity to the ground such as during taxiing, takeoff or landing.

The annunciator panel * includes alternator and low oil pressure indicator lights. When the optional gyro system is installed, the annunciator panel also includes a low vacuum indicator light. The annunciator panel lights are provided only as a warning to the pilot that a system may not be operating properly, and that he should check and monitor the applicable system gauge to determine when or if any necessary action is required.

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 which results in improved radio and electrical equipment operation. Since the alternator output is available all the time, the battery will be charging almost continuously. This will make cold weather starting easier.

In generator systems, the ammeter indicates battery discharge. In the Cherokee electrical system the ammeter displays in amperes the load placed on the alternator. With all electrical equipment except the master switch in the OFF position, the ammeter will indicate 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 2 amperes for a fully charged battery will appear continuously under these conditions. Do not take off with a fully discharged battery as 3 volts are needed to excite the alternator.

* Serial nos. 7525001 and up

2-8

AIRPLANE AND SYSTEMS

REVISED: MAY 22, 1980

CHEROKEE CRUISER

STARTE" • ACCESSOfIIU

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CI'AIt

_ UGHTE"

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I l'OWEIt

SOLENOID

EXTERNAL

POWE"

RECEPTACLE

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ICX.EPIOID

,----,

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MAITU

SWITCH

Alternator and Starter Schematic (Ser. nos. 7425001 through 7425454)

AIRPLANE AND SYSTEMS

REVISED: JUNE 13, 1974 2-9

CHEROKEE CRUISER

STARTER a

ACCESSORIES ALTERNATOR FIELD

5A liN LINE)

STARTER

SOLENOID

STARTER

, r-,

:

I I i.._J

CIQAR

_ UGHTER

WARN

ALT LIGHT

,---------------,

EXTERNAL I

POWER

SOLENOID I

-::-l

EXTERNAL

POWER

RECEPTACLE

AMht£TER

,----..,

~~ER~~J

SOURCE-POWER

RELAY ENERGIZING CIRCUIT

MASTER

SWITCH

2-9a

Alternator and Starter Schematic (Ser. nos. 7525001 and up)

AIRPLANE AND SYSTEMS

ISSUED: JUNE 13, 1974

CHEROKEE CRUISER

The master switch is a split switch with the left half operating the master relay and the right half energizing the alternator. The switch is interlocked so that the alternator cannot be operated without the battery. For normal operation, be sure both halves are turned on.

Maintenance on the alternator should prove to be a minor factor. Should service be required, contact the local Piper Dealer.

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. The artificial horizon and directional gyro are vacuum operated through use of a vacuum pump installed on the engine, while the turn and bank instrument is electrically operated. A vacuum gauge is mounted on the far right side of the instrument panel. A natural separation of the flight group and power group is provided by the placement of the flight group in the upper instrument panel and the power group in the center and lower instrument panels. The radios and circuit breakers are on the right hand instrument panel, and extra circuits are provided for a complete line of optional radio equipment. The microphone is located on the console. 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. 7525001 and up

2-11

AIRPLANE AND SYSTEMS

REVISED: JUNE 13, 1974

.....

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IS 20 21 22 16 23 24 25 26

1. STALL WARNING INDICATOR

2. CLOCK

3. TURN INDICATOR

4. AIRSPEED INDICATOR

5. DIRECTIONAL GYRO

6. ATTITUDE GYRO

7. VERTICAL SPEED INDICATOR

•• ALTIMETER

9. TRANSPONDER

10. MAGNETIC COMPASS

11. MARKER BEACON

12. OMNI" GLIDE SLOPE INDICATORS

13. AUDIO SELECTOR PANEL

14. UHF TRANSCEIVERS

15. ADF RECEIVER

27 28 29 3D 31 32 33 34

16. NAV SELECTOR SWITCH

17. SUCTION GAUGE

18. CIGAR LIGHTER

19. MIKE JACK

20. PHONE JACK

21. AUTOPILOT

22. OMNI COUPLER

23. MAGNETO/STARTER SWITCH

24. PITCH CONTROL

25. CHECKLIST

26. INSTRUMENT CLUSTER

27. TACHOMETER

21. PRIMER

29. MICROPHONE

30. THROTTLE QUADRANT

35 36 31 40 31

31. FRICTION LOCK

32. CARBURETOR HEAT CONTROL

33. AMMETER GAUGE

34. RADIO DIMMING LIGHTS

35. CIRCUIT

BREAKE~

36. CIRCUIT BREAKER COVER (ON

EARLY MODELS ONLY)

37. CLIMATE CONTROL

31. HEAT" DEFROSTER CONTROLS

39. ANNUNCIATOR PANEL (SER. NOS.

7525001 AND UP)

40. ENGINE HOUR METER

( j

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CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

2-12a

AIRPLANE AND SYSTEMS

ISSUED: JUNE 13, 1974

CHEROKEE CRUISER

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.

To prevent bugs and water from entering the pitot and static pressure holes, when the airplane is parked, a cover should be placed over the pitot head. A partially or completely blocked pitot head will give erratic or zero readings on the instruments.

NOTE

During the preflight, check to make sure the pitot cover is removed.

HEATING AND VENTILATING SYSTEM

Heat for the cabin interior and the defroster system is provided by a heater muff attached to the exhaust system. The amount of heat desired can be regulated with the controls located on the far right side of the instrument panel. If unusual odors are noticed, the heat should be shut off and the system inspected for leaks. The airflow may be regulated between the front and rear seats by the use of the levers located on top of the heat ducts next to the control console.

CAUTION

When cabin heat is operated, heat duct surface becomes hot. This could result in burns if arms or legs are placed too close to heat duct outlets or surface.

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. Cabin air is exhausted through an outlet located below the rear seat floor panel. A cabin air blower, which helps to distribute fresh air through the cabin, is available as optional equipment when air conditioning is not installed. This blower is operated by a "FAN" switch with 4 positions -

OFF," "LOW," "MED," or "HIGH."

On the Flite Liner, overhead air outlets are not offered as optional equipment.

2-14

AIRPLANE AND SYSTEMS

REVISED: APRIL 16, 1979

CHEROKEE CRUISER

CABIN FEATURES

For ease of entry and exit and pilot-passenger comfort, the front seats recline and are adjustable fore and aft. A family seat installation which provides two additional seats is available. Each family seat is capable of carrying a full size adult, which gives the Cherokee 140

4-place capability. Optional headrests and vertically adjustable front seats are also available.

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 when they are installed. The shoulder strap is routed over the shoulder adjacent to the windows and attached to the lap strap in the general area of the occupant'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.

The Flite Liner has all of the above features, except there is only one radio installed, and optional headrests, vertically adjustable front seats, and family seats are not available.

BAGGAGE AREA

A 22 cubic foot luggage compartment is located behind the seats in the two-place model and is accessible from the cabin. Maximum baggage capacity is 200 pounds.

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 are primed with etching primer and finished with a durable acrylic lacquer in a variety of tasteful colors to suit individual owners. To keep a new look, economy size "Touch-Up" spray paint cans are available from Piper Dealers.

2-16

AIRPLANE AND SYSTEMS

REVISED: JANUARY 21, 1975

CHEROKEE CRUISER

AIR CONDITIONING*

The air conditioning system is a recirculating air system. The major items include; evaporator, condenser, compressor, blower, switches and temperature controls.

The evaporator is located behind the left rear side of the baggage compartment. This cools the air that is used for air conditioning.

The condenser is mounted on a retractable scoop located on the bottom of the fuselage and to the rear of the baggage compartment area. The scoop extends when the air conditioner is

"ON" and retracts to a flush position when the system is "OFF."

The compressor is mounted on the forward right underside of the engine. It has an electric clutch which automatically engages or disengages the compressor to the belt drive system of the compressor.

An electrical blower is mounted on the aft side of the rear cabin panel. Air from the baggage area is drawn through the evaporator by the blower and distributed through an overhead duct to individual outlets located adjacent to each occupant.

The switches and temperature control are located on the lower right side of the instrument panel in the climate control center panel. The temperature control regulates the temperature of the cabin. Turn the control clockwise for increased cooling, counterclockwise for decreased cooling.

Located inboard of the temperature control is the fan speed switch and the air conditioning "ON-OFF" switch. The fan can be operated independently of the air conditioning.

However, it must be on for air conditioner operation. Turning either switch off will disengage the compressor clutch and retract the condenser door. Cooling air should be felt within one minute after the air conditioner is turned on.

NOTE

If the system is not operating in 5 minutes, turn the system

"OFF" until the fault is corrected.

The "FAN" switch allows operation of the fan with the air conditioner turned "OFF" to aid cabin air circulation if desired. A "LOW," "MED" or "HIGH" flow of air can be selected to the air conditioner outlets located in the overhead duct. The outlets can be adjusted or turned off by each occupant to regulate individual cooling effect.

The "DOOR OPEN" indicator light is located to the left of the radio stack in front of the pilot. The light illuminates whenever the condenser door is open and remains on until the door is closed.

A circuit breaker located on the circuit breaker panel protects the an conditioning electrical system.

*Optional equipment

AIRPLANE AND SYSTEMS

ISSUED: JULY 6, 1973 2-17

CHEROKEE CRUISER

Whenever the throttle is in the full throttle position, it actuates a micro switch which disengages the compressor and retracts the scoop. This is done to obtain maximum power and maximum rate of climb. The fan continues to operate and the air will remain cool for approximately one minute. When the throttle is retarded approximately 114 inch, the clutch will engage and the scoop will extend, again supplying cool, dry air.

PIPER EXTERNAL POWER*

An optional starting installation known as Piper External Power (PEP) is accessible through a receptacle located on the right side of the fuselage aft of the wing. An external battery can be connected to the socket, thus allowing the operator to crank the engine without having to gain access to the airplane's battery. This installation is not available on the Flite Liner.

*Optional equipment

2-18

AIRPLANE AND SYSTEMS

ISSUED: JULY 6, 1973

AIRPLANE FLIGHT MANUAL

FOR

CHEROKEE CRUISER

APPLICABLE TO AIRCRAFT SERIAL NUMBERS 28-7425001 THROUGH 28-7625275

WARNING

EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL

TO APPLICABLE AIRCRAFT. THIS MANUAL REVISED AS INDICATED BELOW

OR SUBSEQUENTLY REVISED IS VALlO FOR USE WITH THE AIRPLANE

IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION.

SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION

MUST BE PROPERLY INSERTED.

MODEL PA-28-140

AIRCRAFT SERIAL NO. REGISTRATION NO.

AIRPLANE FLIGHT MANUAL, REPORT NUMBER VB-557 REVISION __________ _

PIPER AIRCRAFT CORPORATION

APPROVAL SIGNATURE AND STAMP _____________________________________ _

NOTE

THIS MANUAL MUST BE KEPT IN THE AIRPLANE AT ALL TIMES

FAA APPROVED BY: b~

H·. W. BAR HOUSE

PIPER AIRCRAFT CORPORATION

D.O.A NO. SO-l

VERO BEACH, FLORIDA

DATE OF APPROVAL: MAY 14, 1973

APPROVAL BASIS: CAR 3

REPORT: VB-557

MODEL: PA-28-140

AIRPLANE FLIGHT MANUAL

Log of Revisions ............................................................................................................................... 3-iii

Limitations ........................................................................................................................................ 3-1

Procedures .......................................................................................................................................... 3-7

Performance ...................................................................................................................................... 3-9

Supplements ...................................................................................................................................... 3-11

CHEROKEE CRUISER

Log of Revisions ................................................................................................................................. 3-iii

SECTION I

Limitations .......................................................................................... ~ ...................................... 3-1

A. Engines ..................................................................................................................... 3-1

B. Fuel ........................................................................................................................... 3-1

C. Propellers .................................................................................................................. 3-1

D. Power Instruments .................................................................................................... 3-1

E. Airspeed Limitations and Airspeed Instrument Markings

(Calibrated Airspeed) (MPH) ............................................................................. 3-2

F. Maximum Weight ..................................................................................................... 3-2

G. Baggage Capacity ..................................................................................................... 3-2

H. C. G. Range .............................................................................................................. 3-2

1. Maneuvers ................................................................................................................ 3-3

J. Placards .................................................................................................................... 3-3

K. Air Conditioned Airplanes ....................................................................................... 3-6

SECTION II

Procedures ................................................................................................................................. 3-7

SECTION III

Performance .............................................................................................................................. 3-9

SECTION IV

Supplements ............................................................................................................................... 3-11

A. Electric Pitch Trim Installation ............................................................................... 3-15

B. AutoFlite II Installation ............................................................................................ 3-16

C. Air Conditioning Installation ................................................................................... 3-18

D. Piper AutoControl III and/or AutoControl lIIB Installation .................................... 3-19

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

REPORT: 'VB 557 PAGE 3-i

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-557 PAGE 3-ii

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

CHEROKEE CRUISER

AIRPLANE FLIGHT MANUAL LOG OF REVISIONS

Revision Revised Pages

Description and Revision

FAA Approved

Date

Title Added PAC Approval Form.

(NOTE: AIRCRAFT DELIVERED WITH

MANUALS PRIOR TO THIS REVISION

DO NOT REQUIRE THIS REVISION.)

Ju--r--"-

D. H. Trompler

May 29,1974

3-i Added item G. Installation of Piper Auto-

3-3

3-4

3-5

3-11

Control IIIB to Supplements.

Revised Item 1. 2. a., 1. 2. b., and J. I.

Revised Item J. 2.

Revised Items I. and 2.

Added Item G. Installation of Piper Auto-

Control IIIB.

3-19,3-20, Added pages (AutoControl IIIB Supple-

3-21,3-22 ment info added).

3-i

3-5

3-11

3-13

3-14

3-15

3-16

3-17

3-18

3-19

3-20

3-22

3-1

.II( ". dJ.

. r

D. H. Trompler

June I 3, 1974

Under Supplements - deleted existing Items

A., B. and E.; revised remaining Items.

Added "Spins Prohibited" to Item 2. under

Maneuvers Placard for Utility Category with

Air Condo or Vent. Blower.

Deleted existing Items A., B. and E.; revised remaining Items.

Deleted Item A. Electric Pitch Trim Installation (Without Pitch Trim Switch).

Deleted Item B. AutoFlite Installation.

Revised existing Item letter (C. to A.); deleted (With Pitch Trim Switch).

Revised existing Item letter (D. to B.).

Deleted Item E. AutoControl III Installation.

Revised existing Item Letter (F. to C.).

Revised existing Item letter (G. to D.); added

AutoControl III to Title.

Deleted IIIB designation from Items

(J) and (2).

Revised item

(1).

Revised item B. Fuel.

W~JEII~

Ward Evans

Nov. 1, 1974

(.JrvJ€V~

Ward Evans

Nov. 27, 1975

[, '

~1"",1I, ~

"\,

~.;).

'Ward-Evans

April 19, 1976

FAA APPROVED MAY 14, 1973

REVISED: APRIL 19, 1976

REPORT: VB-557 PAGE 3-iii

MODEL: PA-28-140

CHEROKEE CRUISER

AIRPLANE FLIGHT MANUAL LOG OF REVISIONS (cont)

Revision Revised Pages

6 Title

Description and Revision

Added Applicable Serial Numbers.

(NOTE: AIRCRAFT DELIVERED WITH

MANUALS PRIOR TO THIS REVISION

DO NOT REQUIRE THIS REVISION.)

FAA Approved

Date

LJ~~

Ward Evans

Sept. 30, 1977

7 3-1

3-22

Revised item B. Fuel.

Added ending serial number effectivity. tl/~li.~

Ward Evans

July 13, 1984

REPORT: VB-557 PAGE 3-iv

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

REVISED: JULY 13, 1984

CHEROKEE CRUISER

SECTION I

LIMITATIONS

The following limitations must be observed in the operation of this airplane:

A. ENGINE

Lycoming 0-320-E2A or 0-320-E3D

ENGINE LIMITS

For all operations 2700 RPM, 150 HP

B. FUEL

AVGAS ONLY

80/87 Octane Aviation Fuel Minimum Grade

C. PROPELLER

Sensenich M74DM or 74DM6, Maximum diameter 74 inches. minimum diameter 72-112 inches. Static RPM at maximum permissible throttle setting: Not under 2150, not over

2425 for max. allowable weight of 1950 lbs. Not under 2275, not over 2425 for max. allowable weight of 2150 lbs. No additional tolerance permitted.

D. POWER INSTRUMENTS

OIL TEMPERATURE

Green Arc (Normal Operating Range)

Red Line (Maximum)

75°F to 245°F

245° F

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)

60 PSI to 90 PSI

25 PSI to 60 PSI

25 PSI

90 PSI

.5 PSI to 8 PSI

.5 PSI

8 PSI

500 to 2700 RPM

2700 RPM

FAA APPROVED MAY 14, 1973

REVISED: JULY 13, 1984

REPORT: VB-557 PAGE 3-1

MODEL: PA-28-140

CHEROKEE CRUISER

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

171 MPH

140 MPH

129 MPH

115 MPH

(Normal Category) 3.8

(Utility Category) 4.4

No inverted maneuvers approved

AIRSPEED INSTRUMENT MARKINGS

Red Radial Line (Never Exceed)

Yellow Arc (Caution Range)

(Smooth Air Only)

Green Arc (Normal Operating Range)

White Arc (Flap Down Range)

171 MPH (148 KTS)

140 MPH to 171 MPH

(121 KTS to 148 KTS)

64 MPH to 140 MPH

(56 KTS to 121 KTS)

55 MPH to 115 MPH

(48 KTS to 100 KTS)

F. MAXIMUM WEIGHT

Utility Category

Normal Category

1950 LBS

2150 LBS

G. BAGGAGE CAPACITY

At Fuselage Station + 117

At Fuselage Station +133 when modified in accordance with

Piper drawing 66671

200LBS

100LBS

H. C. G. RANGE

The datum used is 78.4 inches ahead of wing leading edge at the intersection of the straight and tapered section.

1. Normal Category

Weight

(Pounds)

2150

1975

1650

Forward Limit

CIn. Aft of Datum)

88.4

85.9

84.0

Rearward Limit

Cln. Aft of Datum)

95.9

2. Utility Category

Weight

(Pounds)

1950

1650

Forward Limit

CIn. Aft of Datum)

85.8

84.0

Rearward Limit

(In Aft of Datum)

86.5

865

REPORT: VB-557 PAGE 3-2

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

CHEROKEE CRIDSER

Straight Line variation between given points.

NOW

It is the responsibility of the airplane owner and/or the pilot to insure that the airplane is properly loaded. See Weight and

Balance Section for loading information.

I. MANEUVERS

1. Normal Category - All acrobatic maneuvers including spins prohibited.

2. Utility Category - Approved maneuvers for Utility Category only.

Entry Speed a. Models Without Air Conditioning or Ventilation Blower

Spins (Flaps Up)

Steep Turns

Lazy Eights

Chandelles

Stall

129 MPH

129 MPH b. Models With Air Conditioning or Ventilation Blower

Steep Turns

Lazy Eights

Chandelles

J. PLACARDS

In full view of the pilot:

Entry Speed

129 MPH

1. Models Without Air Conditioning or Ventilation Blower

"THIS AIRPLANE MUST BE OPERAWD AS A NORMAL OR

UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH

THE OPERATING LIMITATIONS STAWD IN THE FORM OF

PLACARDS, MARKINGS AND MANUALS.

ALL MARKINGS AND PLACARDS ON THIS AIRPLANE

APPLY TO ITS OPERATION AS UTILITY CATEGORY

AIRPLANE. FOR NORMAL AND UTILITY CATEGORY

OPERATIONS, REFER TO THE AIRPLANE FLIGHT

MANUAL.

FOR SPIN RECOVERY, USE FULL RUDDER AGAINST SPIN,

FOLLOWED IMMEDIAWLY BY FORWARD WHEEL.

NO ACROBATIC MANEUVERS (INCLUDING SPINS) ARE

APPROVED FOR NORMAL CAWGORY OPERATIONS."

FAA APPROVED MAY 14, 1973

REVISED: JUNE 13, 1974

REPORT: VB-557 PAGE 3-3

MODEL: PA-28-140

CHEROKEE CRUISER

2. Models With Air Conditioning or Ventilation Blower

"THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR

UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH

THE OPERATING LIMITATIONS STATED IN THE FORM OF

PLACARDS, MARKINGS AND MANUALS.

ALL MARKINGS AND PLACARDS ON THIS AIRPLANE

APPLY TO ITS OPERATION AS A UTILITY CATEGORY

AIRPLANE. FOR NORMAL AND UTILITY CATEGORY

OPERATIONS, REFER TO THE AIRPLANE FLIGHT

MANUAL.

NO ACROBATIC MANEUVERS ARE APPROVED FOR

NORMAL CATEGORY OPERATIONS. SPINS ARE

PROHIBITED FOR BOTH NORMAL AND UTILITY

CATEGORIES."

In full view of the pilot, the following takeoff and landing check lists will be installed:

Fuel on proper tank

Electric fuel pump on

TAKEOFF CHECK LIST

Mixture set

Seat backs erect

Engine gauges checked

Flaps - set

Carb heat off

Fasten belts/hamess

Trim tab - set

Controls - free

Door - latched

Air Conditioner - off

Fuel on proper tank

Mixture rich

Electric fuel pump on

LANDING CHECK LIST

Seat backs erect

Flaps - set (115 mph)

Fasten belts/hamess

Air Conditioner - off

The "AIR COND OFF" item in the above takeoff and landing check lists is mandatory for air conditioned aircraft only.

In full view of the pilot, in the area of the air conditioner control panel when air conditioner is installed:

"WARNING - AIR CONDITIONER MUST BE OFF TO INSURE

NORMAL TAKEOFF CLIMB PERFORMANCE."

REPORT: VB-557 PAGE 3-4

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

REVISED: JUNE 13, 1974

CHEROKEE CRUISER

Adjacent to upper door latch:

"ENGAGE LATCH BEFORE FLIGHT."

On aft side of baggage compartment:

"UTILITY CATEGORY OPERATION - NO BAGGAGE OR

AFT PASSENGERS ALLOWED. NORMAL CATEGORY

OPERATION - SEE AIRPLANE FLIGHT MANUAL WEIGHT

AND BALANCE SECTION FOR BAGGAGE AND AFT

PASSENGER LIMITATIONS."

On the instrument panel in full view of the pilot when the oil cooler winterization kit is installed:

"OIL COOLER WINTERIZATION PLATE TO BE REMOVED

WHEN AMBIENT TEMPERATURE EXCEEDS SO°F."

On the instrument panel in full view of the pilot when the AutoFlite is installed:

"FOR HEADING CHANGES: PRESS DISENGAGE SWITCH

ON CONTROL WHEEL. CHANGE HEADING. RELEASE

DISENGAGE SWITCH."

In full view of the pilot:

UTILITY CATEGORY ONLY

ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING:

1. Models Without Air Conditioning or Ventilation Blower

Entry Speed

STALL SPINS (FLAPS UP)

STEEP TURNS

LAZY EIGHTS

CHANDELLES

129 MPH

2. Models With Air Conditioning or Ventilation Blower

Entry Speed

SPINS PROHIBITED

STEEP TURNS

LAZY EIGHTS

CHANDELLES

129 MPH

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

REPORT: VB-557 PAGE 3-5

MODEL: PA-28-140

CHEROKEE CRUISER

In full view of the pilot:

"ROUGH AIR OR MANEUVERING SPEED - 129 MPH."

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."

K. AIR CONDITIONED AIRPLANES

Air Conditioner must be off for takeoff and landing.

REPORT: VB-557 PAGE 3-6

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

CHEROKEE CRUISER

SECTION II

PROCEDURES

1. The stall warning system is inoperative with the master switch off.

2. The electric fuel pump must be on for both takeoff and landing.

3. Except as noted above, all operating procedures for this airplane are normal.

4. Air Conditioned Models only: Warning - The air conditioner must be off to insure normal takeoff performance.

FAA APPROVED MAY 14, 1973 REPORT: VB-557 PAGE 3-7

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-557 PAGE 3-8

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

CHEROKEE CRUISER

SECTION III

PERFORMANCE

All performance is gi ven for a weight of 2150 pounds.

Loss of altitude during stalls can be as great as 200 feet, depending on configuration and power.

Stalling speeds, in mph, power off, versus angle of bank (Calibrated Airspeed):

Angle of Bank

Flaps Up

Flaps Down

0°

Air Conditioner Models only:

When the full throttle position is not used or in the event of a malfunction which causes the compressor to operate and the condenser door to remain extended, a decrease in rate of climb of as much as 100 fpm can be expected at all altitudes.

FAA APPROVED MAY 14, 1973 REPORT: VB-5S7 PAGE 3-9

MODEL: PA-28 140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-557 PAGE 3-10

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

CHEROKEE CRUISER

SECTION IV

SUPPLEMENTS

NOTE

A FLIGHT MANUAL SUPPLEMENT IS REQUIRED TO BE IN

THE AIRPLANE FLIGHT MANUAL ONLY IF THE

EQUIPMENT WHICH IS THE SUBJECT OF THE

SUPPLEMENT IS INSTALLED.

A. Electric Pitch Trim Installation

B. AutoFlite II Installation

C. Air Conditioner Installation

D. Piper AutoControl III and/or AutoControl nIB Installation

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

REPORT: VB-557 PAGE 3-11

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-557 PAGE 3-12

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

REPORT: VB-557 PAGE 3-13

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFf BLANK

REPORT: VB-557 PAGE 3-14

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

CHEROKEE CRUISER

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

10° pitch change and 30 ft altitude variation.

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

REPORT: VB-557 PAGE 3-15

MODEL: PA-28-140

CHEROKEE CRUISER

B. AUTOFLITE II INSTALLATION

I. LIMITATIONS

AutoFlite off for takeoff and landing.

2. PROCEDURES a. Normal Operation

Refer to Manufacturer's Operation Manual. b. Emergency Operation

(I) In case of malfunction, PRESS disconnect 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 100 ft altitude loss.

(5) In approach configuration malfunction, I second delay results in 10° bank and 0 ft altitude loss.

REPORT: VB-557 PAGE 3-16

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

REPORT: VB-557 PAGE 3-17

MODEL: PA-28-140

CHEROKEE CRUISER

C. AIR CONDITIONER INSTALLATION

Prior to takeoff, the air conditioner should be checked for proper operation as follows:

1. Check aircraft master switch on.

2. Turn the air conditioner control switch to "ON" and the fan switch to one of the operating positions - the "AIR COND DOOR OPEN" warning light will turn on, thereby indicating proper air conditioner condenser door actuation.

3. Turn the air conditioner control switch to OFF - the "AIR COND DOOR

OPEN" warning light will go out, thereby indicating the air conditioner condenser door is in the up position.

4. If the "AIR COND DOOR OPEN" light does not respond as specified above, an air conditioner system or indicator bulb malfunction is indicated and further investigation should be conducted prior to flight.

The above operational check may be performed during flight if an in flight failure is suspected.

WARNING

The air conditioner must be off to insure normal takeoff performance.

REPORT: VB-557 PAGE 3-18

MODEL: PA-28-140

FAA APPROVED MAY 14, 1973

REVISED: NOVEMBER 1, 1974

CHEROKEE CRUISER

D. PIPER AUTOCONTROL III AND/OR AUTOCONTROL IIIB INSTALLATION

1. LIMITATIONS a. Autopilot OFF during takeoff and landing. b. Autopilot use prohibited above 140 MPH CAS.

2. PROCEDURES a. PREFLIGHT

(1) Roll Section

(a) Place Radio Coupler in "Heading" mode and place A/P

ONIOFF 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 turn, 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 Heading 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 AlP ON/OFF switch to the "OFF" position. b. IN-FLIGHT

(1) 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 AlP

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 HDG knob in, rotate to aircraft heading. Place the console HDG 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 HDG mode the maximum bank angles are limited to approximately 20° and single command, heading changes should be limited to 150°. (HDG Indice not more than 150° from actual aircraft heading.)

FAA APPROVED JUNE 13, 1974

REVISED: NOVEMBER 1, 1974

REPORT: VB-557 PAGE 3-19

MODEL: PA-28-140

CHEROKEE CRUISER

(4) VOR

(a) To Intercept:

I. 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, (112 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.

I. 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:

(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 HDG 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.

(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.

REPORT: VB-557 PAGE 3-20

MODEL: PA-28-140

FAA APPROVED JUNE 13, 1974

CHEROKEE CRUISER

NOTE

For precise tracking over OMNI station, without "S" turn, position coupler mode selector to HDG mode just prior to station passage. If holding pattern is desired, position coupler mode selector to HDG mode at station passage inbound and select outbound heading in direction of turn. After elapsed time, dial inbound course on Course Selector D.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.

(7)

(c) When aircraft heading is 45° to ILS inbound course dial inbound course on Course Selector D.G. and position coupler mode selector to LOC NORM mode.

(d) At the missed approach point (M.A.P.), or when missed approach is elected, position coupler mode selector to HDG mode and execute missed approach procedure.

LOC Approach - Back Course (Reverse)

(a) To intercept dial ILS Back Course outbound heading on

Course Selector D.G. When stabilized, position coupler mode selector to LOC NORM mode.

(b) After interception and when beyond fix, position coupler mode selector to HDG 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 112 mile from runway, position coupler mode selector to HDG mode to prevent "S" turn over ILS station near runway threshold.

(e) Missed approach - same as Front Course. (See (6) d)

FAA APPROVED JUNE 13, 1974 REPORT: VB-557 PAGE 3-21

MODEL: PA-28-140

CHEROKEE CRUISER c. EMERGENCY OPERATION

(1) In an emergency the AutoControl can be disconnected by:

(a) Placing the AlP ONIOFF switch to the "OFF" position.

(b) Pulling the Autopilot circuit breaker (aircraft SIN 28-7625001 through 28-7625275).

(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 100 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 10° bank and 10 foot altitude loss.

3. PERFORMANCE

No change.

REPORT: VB-557 PAGE 3-22

MODEL: PA-28-140

FAA APPROVED JUNE 13, 1974

REVISED: JULY 13, 1984

F.A.A. APPROVED

EMERGENCY PROCEDURES

NONE APPLICABLE TO THIS AIRPLANE

EMERGENCY PROCEDURES

Introduction ........... ........ .... ........ .... ................ .... ... .............. ............ ............................ ........ ....... ..... 4-1

Engine Power Loss During Takeoff .......... ........ .... .... ...... ....... ... ..................... ...... ........ ...... ............ 4-1

Engine Power Loss In Flight .......................................................................................................... 4-2

Power Off Landing ......................................................................................................................... 4-2

Spins ............................................................................................................................................... 4-3

Open Door ...................................................................................................................................... 4-3

Fire.................................................................................................................................................. 4-4

Loss of Oil Pressure........................................................................................................................ 4-5

Loss of Fuel Pressure...................................................................................................................... 4-5

High Oil Temperature ..................................................................................................................... 4-5

Alternator Failure .................................... ....................................................................................... 4-6

Engine Roughness......... .............. ......................... ............ ........ ........ ......... .... ..... ......... ................... 4-6

4-i

CHEROKEE CRUISER

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.

EMERGENCY PROCEDURES

ISSUED: JULY 6,1973 4-1

CHEROKEE CRUISER

ENGINE POWER LOSS IN FLIGHT

Complete 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 80 MPH lAS, and if altitude permits, proceed as follows:

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 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 restored 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.

POWER OFF LANDING

If loss of power occurs at altitude, trim the aircraft for best gliding angle (80 MPH lAS -

Air Condo OFF) and look for a suitable field. If measures taken to restore power are not effective, and if time permits, check your charts for airports in the immediate vicinity; it may be possible to land at one if you have sufficient altitude. If possible, notify the FAA by radio of your difficulty and intentions. If another pilot or passenger is aboard, let 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. Excess altitude may be lost by widening your pattern, using flaps or slipping, or a combination of these.

4-2

EMERGENCY PROCEDURES

ISSUED: JULY 6, 1973

CHEROKEE CRUISER

Touchdowns should normally be made at the lowest possible airspeed, with full flaps.

When committed to landing:

I. Ignition - Off

2. Master Switch - Off

3. Fuel Selector - Off

4. Mixture - Idle Cut-Off

5. Seat Belt (and harness if available) - Tight

SPINS

Intentional spins are prohibited in the normal category airplane and the utility category airplane when air conditioning is installed. For approved maneuvers as a utility category airplane, refer to the Flight Manual. If a spin is inadvertently entered, immediately use the following recovery procedures:

I. 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:

1. Slow aircraft to 100 MPH lAS.

2. Cabin Vents - Close

3. Storm Window - Open

4. If upper latch 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 6, 1973 4-3

CHEROKEE CRUISER

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

4-4

EMERGENCY PROCEDURES

ISSUED: JULY 6, 1973

CHEROKEE CRUISER

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 Joss of pressure.

EMERGENCY PROCEDURES

ISSUED: JULY 6, 1973 4-5

CHEROKEE CRUISER

ALTERNATOR FAILURE

Loss of alternator output is detected through a 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.

I. Reduce Electrical Load.

2. Alternator Circuit Breakers - Check

3. "Alt" Switch - Off (for I 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 which is indicated by a drop in RPM, and may be accompanied by a slight loss of airspeed or altitude. If too much ice is allowed to accumulate, restoration of full power may not be possible; therefore, prompt action is required.

Turn carburetor heat on (See Note). RPM will decrease slightly and roughness will increase.

Wait for a decrease in engine roughness or an increase in RPM, indicating ice removal. If no change in approximately one minute, return the carburetor heat to COLD. If the engine is still rough, try steps below:

I. Mixture - Adjust for maximum smoothness. Engine will run rough if too rich or too lean.

2. 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 be worse than no heat at all, since it may partially melt ice, which will refreeze in the intake system.

When using carburetor heat, therefore, always use full heat, and when ice is removed return the control to the full cold position.

4-6

EMERGENCY PROCEDURES

REVISED: JUNE 13, 1974

WEIGHT AND BALANCE

FOR

CHEROKEE CRUISER

APPLICABLE TO AIRPLANE SERIAL NUMBERS 28-7425001 THROUGH 28-7625275

WARNING

EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS REPORT TO

APPLICABLE AIRCRAFT. THIS REPORT REVISED AS INDICATED BELOW OR

SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE

IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION.

SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION

MUST BE PROPERLY INSERTED.

MODEL PA-28-140

PIPER AIRCRAFT CORPORATION

APPROVALSIGNATUREANDSTAMP _________________________ _

ISSUED: MAY 14,1973

REVISED: SEPTEMBER 30, 1977

REPORT: VB-546

MODEL: PA-28-140

CHEROKEE CRUISER

INDEX - WEIGHT AND BALANCE

Log of Revisions........................................... .................................................................................. 5-iii

Weight and Balance ........................................................................................... ............ ................. 5-1

Weight and Balance Data - Weighing Procedure............................................................................ 5-3

Weight and Balance ........................................................................................................................ 5-7

C.G. Range and Weight Instructions .............................................................................................. 5-8

Sample Loading Problem ............................................................................................................... 5-9

Maximum Allowable Baggage ....................................................................................................... 5-11

Equipment List ............................................................................................................................... 5-15

A. Propeller and Propeller Accessories ................................................... ................... ............ 5-15

Engine and Engine Accessories.........................................................................................

Landing Gear and Brakes ..................................................................................................

5-16

5-17

Electrical Equipment .........................................................................................................

Instruments ........................................................................................................................

Miscellaneous ....................................................................................................................

Engine and Engine Accessories (Optional Equipment) ....................................................

Electrical Equipment (Optional Equipment) .....................................................................

5-18

5-19

5-20

5-21

5-22

Instruments (Optional Equipment) .................................................................................... 5-24

Autopilots (Optional Equipment) ...................................................................................... 5-25

Radio Equipment (Optional Equipment)........................................................................... 5-26

Miscellaneous (Optional Equipment) ................................................................................ 5-29

ISSUED: MAY 14, 1973 REPORT: VB-546 PAGE 5-i

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-546 PAGE 5-ii

MODEL: PA-28-140

ISSUED: MAY 14,1973

CHEROKEE CRUISER

WEIGHT AND BALANCE LOG OF REVISIONS

Revision Revised Pages

5-16

5-18

5-20

5-22

5-27

5-28

5-29

5-30

Title

5-16

5-18

5-20

5-21

5-23

5-24

5-25

Description and Revision Approved Date

Revised Oil Cooler Weight and Moment.

Revised Voltage Regulator Weight and

Moment; Revised Battery Weight and

Moment.

Revised Baggage Tie Down Straps Weight and

Moment; Revised Toe Brakes Weight and

Moment and added dwg. no.

Revised Battery Weight and Moment.

Revised Narco Audio Panel Weight, Arm and

Moment; Revised MBT-12-R Marker

Beacon Weight, Arm and Moment.

Revised -10, -12 Microphone Weights, Arms and Moments.

Revised Nose Wheel Fairing and Main Wheel

Fairing Weights, Arms and Moments;

Changed Jump Seat to -4 Install.; Revised

Ash Trays Weight and Moment.

Removed Baggage Tie Down Straps; Revised

Right and Left Vert, Adj. Front Seat

Weights, Arms and Moments; Revised

Ground Vent. Blower; Added Corrosive

Resistant Kit

Added PAC Approval Form.

(NOTE: AIRCRAFT DELIVERED WITH

MANUALS PRIOR TO THIS REVISION

DO NOT REQUIRE THIS REVISION.)

October 22, 1973

~cJ;/..M~

May 29,1974

~:2 :',,-

Added Oil Filters and footnote.

Added Annunciator Lights and footnote.

Revised Inertia Safety Belts weights, moment and part no.

Added Airborne Vacuum Pump (PAC 79399-0); added Low Vacuum Annunciator Light; added Airborne Vacuum Regulator

(#2H3-19); added footnotes.

Added Overhead Red Panel Lights and Instrument Panel Lights.

Added Encoding Altimeter and footnote.

Added Autocontrol IllB and footnotes; revised nomenclature (Console #IC338).

June 13, 1974

ISSUED: MAY 14, 1973

REVISED: JUNE 13, 1974

REPORT: VB-S46 PAGE S-iii

MODEL: PA-28-140

CHEROKEE CRUISER

WEIGHT AND BALANCE LOG OF REVISIONS (coot)

Revision Revised Pages

3 (cont)

Description and Revision Approved Date

5-26

5-27

5-28

5-28a,5-28b,

5-28c, 5-28d

5-29

Revised nomenclature (King KX175); added footnote.

Added footnote.

Revised nomenclature (King KMA-20 Audio

Panel).

Added pages (info for ser. nos. 7525001 and up).

Revised Inertia Safety Belts part no.; revised Assist Strap and Coat Hook dwg. no., added Assist Strap.

5-14

5-21

5-28a

5-5

5-30

Revised Utility Category Aft e.G. Limit.

Revised Airborne Vacuum Pump Moment.

Revised King Dual KNI-520 Weight.

Revised equations.

Added two Overhead Vent Systems.

Nov. 1,1974 o-tqf~

Jan. 21, 1975

5-14

5-16

5-22

5-24

5-30

5-31

5-22

Revised e.G. Range and Weight graph.

Deleted Chrysler Alternator.

Revised Dwg. No. (Piper Pitch Trim) to -2; added -3; added footnote.

Added Engine Hour Meter and footnote.

Added 79590-0 left Front Seat; added

79590-1 right Front Seat; added 79337-18

Headrest.

Added Stainless Steel Control Cables.

Revised Rotating Beacon desc.

May 16, 1975

CIIf~·

c.~"Jt.

July 18, 1975

8 5-24

5-28

5-28a

Revised Clock.

Revised Automatic Locator Transmitter.

Added KN6l and KN65A DME's.

Nov. 27, 1975

~~.

9 5-28

REPORT: VB-546 PAGE 5-iv

MODEL: PA-28 140

Added Automatic Locator Transmitter. July 19,1976

t"'!.~

•

L L,

ISSUED: MAY 14, 1973

REVISED: JULY 19, 1976

CHEROKEE CRUISER

WEIGHT AND BALANCE LOG OF REVISIONS (cont)

Revision Revised Pages

10 Title

5-1

5-3

5-4

5-1

Description and Revision

Added Applicable Serial Numbers.

(NOTE: AIRCRAFT DELIVERED WITH

MANUALS PRIOR TO THIS REVISION

DO NOT REQUIRE THIS REVISION.)

Revised Weight and Balance info.

Added Caution; relocated para. 2.b. to pg.5-4

Added para. 2.b. from pg. 5-3.

Revised Weight and Balance info.

Approved Date

Sept. 30, 1977

(J,.('. f~·

1/).

May 22,1980

+laPJ~

July 13, 1984 t.J~~

5-1

5-3,

5-7

5-15

5-16

5-18,

5-21,

5-22

5-24

5-25

5-26

5-28a,

5-28b

5-28c

Revised Weight and Balance info.

Revised Weight and Balance Data info.

Revised Equipment List.

Added Niagara N.D.M 20002A to existing oil cooler description: added ending serial effectivity.

Added ending serial number effectivity.

Revised Encoding Altimeter Moment: added ending serial number effectivity.

Added ending serial number effectivity.

Revised King KI 214 ( ) VORJLOCIGS

Ind. Moment.

Added ending serial number effectivity.

Revised Sense Antenna and Cable #1

Moment; added ending serial number effectivity.

ISSUED: SEPTEMBER 30, 1977

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-v

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-S46 PAGE S-vi

MODEL: PA-28-140

ISSUED: SEPTEMBER 30, 1977

CHEROKEE CRUISER

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 the approved operating range (envelope). Although the airplane offers flexibility of loading, it cannot be flown 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 e.G. is too far forward in any airplane, it may be difficult to rotate for takeoff or landing. If the e.G. is too far aft the airplane may rotate prematurely on takeoff or tend to pitch up during climb. Longitudinal stability will be reduced. This can lead to inadvertent stalls and even spins, and spin recovery becomes more difficult as the center of gravity moves aft of the approved limit.

A properly loaded airplane, however, will perform as intended. Before the airplane is licensed, it is weighed, and a licensed empty weight and e.G. location is computed (licensed empty weight consists of the standard empty weight of the airplane plus the optional equipment). Using the licensed empty weight and C.G. location the pilot can determine the weight and C.G. position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope.

The licensed empty weight and C.G. location are recorded in the Weight and Balance Data

Form (Page 5-7). The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic responsible for the work is required to compute a new licensed empty weight and C.G. position and to write these in the Aircraft Log Book and the

Weight and Balance Data Form. 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 within allowable limits. Check calculations prior to adding fuel to insure against improper loading.

The following pages are forms used in weighing an airplane in production and in computing licensed empty weight, e.G. position, and useful load. Note that the useful load includes usable fuel, baggage, cargo and passengers. Following this is the method for computing takeoff weight and e.G.

ISSUED: MAY 14,1973

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-1

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-546 PAGE 5-2

MODEL: PA-28-140

ISSUED: MAY 14, 1973

CHEROKEE CRUISER

WEIGHT AND BALANCE DATA

WEIGHING PROCEDURE

At the time of licensing Piper Aircraft Corporation provides each airplane with the licensed empty weight and center of gravity location. This data is on Page 5-7.

The removal or addition of equipment or airplane modifications can affect the licensed empty weight and empty weight center of gravity. The following is a weighing procedure to determine 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.

CAUTION

Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to insure no air exists in the fuel supply lines. 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.

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-3

MODEL: PA-28-140

CHEROKEE CRUISER b. Level airplane (see diagram) by deflating nose wheel tire, to center bubble on level.

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

Reading Tare

Net

Weight Scale Position and Symbol

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-28-140 airplane when airplane is level (See Item 2). t--C.G.Arm-~

).04---78.4 ---i~

Level Points

(Fuselage Left Side)

REPORT: VB-546 PAGE 5-4

MODEL: PA-28-140

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

REVISED: APRIL 16, 1979

CHEROKEE CRUISER 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: e.G. Arm

78.4 + A - BCN)

C. G. Arm

78.4 + (

) ,,-C -:------,-)

_,...---L) = inches

5. LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY

Weight Arm Moment

Empty Weight (as weighed)

Unusable Fuel (3 pints)

Licensed Empty Weight

+ 2.2 103.0 + 227

ISSUED: MAY 14, 1973

REVISED: JANUARY 21, 1975

REPORT: VB-546 PAGE 5-5

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-546 PAGE 5-6

MODEL PA-28-140

ISSUED: MAY 14, 1973

CHEROKEE CRUISER

WEIGHT AND BALANCE DATA

MODEL PA-28-140 CHEROKEE

Airplane Serial Number 28 -

Registration Number

Date

AIRPLANE EMPTY WEIGHT

C. G. Arm

Weight X (Inches Aft = Moment

(Lbs) of Datum) (In-Lbs) Item

*Empty Weight

Unusable Fuel (3 pints)

Actual

Computed

Standard Empty Weight

Optional Equipment

2.2 103.0 227

Licensed Empty Weight

*Empty weight is defined as dry empty weight (including paint and hydraulic fluid) plus

1.8 lbs undrainable engine oil.

AIRPLANE USEFUL LOAD

(Gross Weight) - (Licensed Empty Weight)

Useful Load

Normal Category:

Utility Category:

(2150Ibs)

(1950Ibs)

(

( lbs) lbs)

= lbs

THIS LICENSED EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE

AIRPLANE AS LICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT

RECORD WHEN ALTERATIONS HAVE BEEN MADE.

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-7

MODEL: PA-28-140

CHEROKEE CRUISER

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 e.G. location.

5. By using the figures of Item 1 and Item 4, locate a point on the e.G. range and weight graph. If the point falls within the e.G. envelope, the loading meets the weight and balance requirements.

NOTE

With optional jump seats installed, aft passenger weight is restricted only by airplane weight and balance limitations (See

Page 5-14). For baggage allowance, see Page 5-11.

REPORT: VB-546 PAGE 5-8

MODEL: PA-28-140

ISSUED: MAY 14, 1973

CHEROKEE CRUISER

SAMPLE LOADING PROBLEM (Normal Category)

Weight

(Lbs)

Arm Aft

Datum

(Inches)

Licensed Empty Weight

Oil (8 quarts)

Pilot and Front Passenger

Passengers, Aft *

Fuel (50 Gal. Maximum)

Baggage * Area 1

Baggage * Area 2

Total Loaded Airplane

340

32.5

85.5

117.0

95.0

117.0

133.3

Moment

(In-Lbs)

488

29070

The center of gravity (e.G.) of this sample loading problem is at datum line. Locate this point ( inches aft of the

) on the e.G. range and weight graph. Since this point faIls 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.

*Utility Category Operation

Normal Category Operation

No baggage or aft passengers all owed.

See Page 5-11.

ISSUED: MAY 14, 1973 REPORT: VB-546 PAGE 5-9

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-546 PAGE 5-10

MODEL: PA-28-140

ISSUED: MAY 14, 1973

MAXIMUM ALLOWABLE BAGGAGE

CHEROKEE CRUISER

A. Maximum Allowable Baggage Capacity Area

<D =

200 lbs.

B. Maximum Allowable Baggage Capacity Area

= 100 lbs.

Aircraft are eligible for lOO-lb maximum baggage in this area when modified in accordance with Piper drawing

66671.

ISSUED: MAY 14, 1973 REPORT: VB-546 PAGE 5-11

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-546 PAGE 5-12

MODEL: PA-28-140

ISSUED: MAY 14, 1973

CHEROKEE CRUISER

LOADING GRAPH

450

400

350

:: c

<

..J en c z

....

::t c:I

300

250

200

150

100

/

L v:

V /~

/. V ....

«j

/

.~o

<t"'# r,:-"'~

/ «~er:::/

/

/ /

/1 eO'"

~;/

/ e~($

~~ ~",':t/'

25 r,:-cf

5 10 15 20 30 35 40

(S)

~e,// ...--

45 50

MOMENT/1000 (POUNDS-INCHES)

ISSUED: MAY 14, 1973 REPORT: VB-546 PAGE 5-13

MODEL: PA-28-140

CHEROKEE CRUISER

C. G. RANGE AND WEIGHTS

2200

2000 en

C z

~ l-

5:2 w

1800

1600

"'"

, /

/ '

" ,

. /

Utility Category

Normel Category

1400

1200

84 86 88 90

INCHES AFT DATUM

92 94 96

REPORT: VB-546 PAGE 5-14

MODEL: PA-28-140

ISSUED: MAY 14, 1973

REVISED: MAY 16, 1975

CHEROKEE CRUISER

EQUIPMENT LIST

The following is a list of equipment which may be installed in the PA-28- I 40. Items marked with an "X" are items installed when the airplane was licensed by the manufacturer.

Item Item

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

A. Propeller and Propeller Accessories

- -

Propeller, Sensenich 74DM6-0-SS

- - -

Spinner and Attachment Plates

Installation PAC Dwg. 995 I 6

30.0

2.0

10.1

S.O

303

TC P920

TC 2AI3

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-15

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

B. Engine and Engine Accessories

Engine - Lycoming Model

0-320-E3D

Fuel Pump, Electric Auxiliary

Bendix Model 478360

Fuel Pump. Engine Driven

Lycoming Dwg. No. 75246

Oil Cooler, Harrison #C-8526250 or Niagara N.D.M. 20002A

Piper Dwg. 18622

Air Filter, Fram Model CA -161

PL or Purolator AFP-2

Starter - Lycoming #76210

Prestolite MZ4204

Oil Filter - Lycoming**

#75528 (AC#OF5578770)

Oil Filter - Lycoming**

#LW-13743 (Champion

#CH-48110

Weight

Lhs.

ArmMt

Datum Moment

Cert.

Basis

265.2

1.8

1.6

26.5

41.8

41.3

1.9

*17.0

3.3

2.8

18.1

20.1

19.5

40.5

7028 TC274

75 TC2A13

66 TC274

34 TC2A13

18 TC2A13

332 TC274

134 TC 2A13

113 TC 2A13

*Included in Engine Weight.

**Serial nos. 28-7525001 through 28-7625275

REPORT: VB-546 PAGE 5-16

MODEL: PA-28-140

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

Item Item

C. Landing Gear and Brakes

- - -

Two Main Wheel Assemblies

6.00 - 6

(a) Cleveland Aircraft Products

(2) Wheel Assembly No. 40-86

(2) Brake Assembly No. 30-55

(b) Two Main 4-Ply Rating Tires

6.00 - 6 with Regular Tubes

- -

One Nose Wheel 6.00 - 6

(a) Cleveland Aircraft Products

Wheel Assembly No. 38501

(Less Brake Drum)

(b) One Nose Wheel 4-Ply Rating

Tire 6.00 - 6 with Regular

Tubes

CHEROKEE CRUISER

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

32.0

12.5

109.6

34.8

3507

435

TC 2AI3

TC 2Al3

ISSUED: MAY 14, 1973 REPORT: VB 546 PAGE 5-17

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

D. Electrical Equipment

Stall Warning Device, Safe

Flight Instrument Corporation,

No. C52207-4

Voltage Regulator, Wico

Electric No. X 16300B

Battery 12V, 25 A.H.,

Rebat Model S-25

Overvoltage Relay, Wico

Electric No. X 16799

Annunciator Lights*

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

80.2

56.9

21.9 114.9

60.4

61.0

16 TSO C54

51 TC 2AD

2516 TC 2A13

TC 2AD

TC 2A13

*Serial nos. 28-7525001 through 28-7625275

REPORT: VB-546 PAGE 5-18

MODEL: PA-28-140

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

Item Item

E. Instruments

Compass - Piper Dwg. 67462-4

Airspeed Indicator -

Piper Dwg. 63205

- - -

Tachometer - Piper

Dwg. 62177-2, -3 or-8

- - - -

Engine Cluster .. Piper

Dwg.95241-17

Altimeter - Piper

PS50008-2 or -3

- -

Ammeter - Piper Dwg. 66696

CHEROKEE CRUISER

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

.9 64.9

1.0

66.8

66.2

67.4

65.9

67.4

58 TSO C7c

40 TSO C2b

46 TC 2A13

54 TC 2A13

TSO CIOb

TC 2A13

ISSUED: MAY 14, 1973 REPORT: VB-546 PAGE 5-19

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

F. Miscellaneous

- - -

Forward Seat Belts (2)

PS50039-4-2A .75 lbs. each

Inertia Safety Belts (2)

PS50039-4-16 .75 lbs. each

Baggage Tie Down Straps

Piper Dwg. 66804 & 66805

Flight Manual & Logs

Tow Bar, Piper Dwg.

99458

Toe Brakes (Dual), Piper

Dwg. 63476-3 & 63473-8

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

1.5 86.9

1.5 119.6

1.2

2.6

118.0

95.1

1.3 103.5

11.0 54.6

130 TSO C22

179 TC 2AI3

142

247

TC 2AI3

135 TC 2Al3

601 TC 2AI3

REPORT: VB-546 PAGE 5-20

MODEL: PA-28-140

ISSUED: MAY 14,1973

REVISED: JUNE 13, 1974

Item Item

G. Engine and Engine Accessories

(Optional Equipment)

- - - - -

Vacuum Pump, Airborne Mfg.

Co., Model No. 200cc and

Drive

- - -

Starter - Lycoming 76211

(Prestolite MZ4206) (Weight

18.0 lbs.)

- - -

Oil Filter - Lycoming **

75528 (AC#OF5578770)

- - - '

Oil Filter- Lycoming **

#LW-13743 (Champion

#CH-48 1 1 0)

Vacuum Regulator, Airborne **

Mfg. Co., # 133A4

- - - -

Vacuum Filter, Airborne

Mfg. Co., 1J7-1

Vacuum Pump, Airborne

Mfg. Co., Model 211 cc and

Drive, PAC 79399-0

- - -

Low Vacuum Annunciator Light ***

Vacuum Regulator, Airborne ***

Mfg. Co., # 2H3-19

CHEROKEE CRUISER

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

5.0

* 1.0

3.3

2.8

3.2

Neglect

37.0

19.5

40.5

57.0

37.0

57.0

185

134

118

TC 2AI3

TC274

TC 2AI3

113 TC 2AI3

34 TC 2AI3

17 TC 2AI3

TC 2AI3

TC 2A13

TC 2AI3

*Weight and moment difference between standard and optional equipment.

**Serial nos. 28-7425001 through 28-7425454

***Serial nos. 28-7525001 through 28-7625275

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-21

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

H. Electrical Equipment (Optional

Equipment)

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

Rotating Beacon

Landing Light, G.E.

Model 4509

Navigation Lights (2)

Grimes Model A 1285

(Red and Green)

Navigation Light (Rear)

(I) Grimes Model A2064-1 073

(White)

Battery 12V, 35 A.H.

Rebat R-35 (Weight 27.2 lbs.)

Cabin Speaker, SB-15052 or

6EU 1937, Quincy Speaker Co.,

Oakton, Ind.

Auxiliary Power Receptacle

Piper Dwg. 65529

External Power Cable,

Piper Dwg. 62355-7

Piper Pitch Trim,

Piper Dwg. 67496-2

Piper Dwg. 67496-3**

Heated Pitot Head,

Piper Dwg. 69041-5

Anti-Collision Lights,

Whelen Engineering Co.,

Piper Dwg. 99033-2 or -5

Power Supply, Model HS

No. A412A-14 (with

Fin Light only)

1.5 263.4

.5 18.1

.4 106.6

.2 281.0

* 5.3 114.9

.8 104.0

3.0 133.0

4.6 117.0

4.3

155.3

.4 100.0

2.3 198.0

*Weight and moment difference between standard and optional equipment

**Serial nos. 28-7525096 through 28-7625275

395 TC 2A13

9 TC 2AI3

43 TSO C30b

56 TSO C30b

609 TC 2A13

83 TC 2A13

399 TC 2A13

538 TC 2A13

668

TC 2A13

40 TC 2A13

455 TC 2AI3

REPORT: VB-546 PAGE 5-22

MODEL: PA-28-140

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

Item Item

H. Electrical Equipment (Optional

Equipment) (cont)

-_._-

Light. Fin Tip A470

- - -

Cable, Fin Light

A417-1/151

- - - -

Power Supply Model HD

T3 A413 (with Fin and

Wing Lights)

- - - -

Lights, Wing Tip (2)

(0.15 lbs. each) No.

429 PR or PG

- - -

Cable Wing Lights

A417-J/388 & A417-J/326

- - -

Overhead Red Panel Lights (2)

Grimes 15-0083-7

- - - -

Instrument Panel Lights

CHEROKEE CRUISER

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

3.0

263.4

230.7

198.0

.3 106.6

2.0 115.6

99.0

67.8 lOS

594

TC 2AI3

TC 2A13

TC 2Al3

32 TC 2AI3

231 TC 2A13

TC 2Al3

ISSUED: MAY 14,1973

REVISED: JUNE 13, 1974

REPORT: VB-546 PAGE 5-23

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

I. Instruments (Optional Equipment)

Suction Gauge, Piper Dwg.

99480-0 or-2

Vertical Speed, Piper Dwg.

99010-2, -4 or -5

Vertical Speed, Piper Dwg.

99010-3

Attitude Gyro, Piper Dwg.

99002-2, -3, -4 or -5

Directional Gyro, Piper

Dwg. 99003-2, -3, -4 or -5

Air Temperature Gauge,

Piper Dwg. 99479-0 or-2

Clock

Tru-Speed Indicator,

Piper Dwg. 62143 or 62143-12

Turn and Slip Indicator,

Piper PS50030-2 or-3

Manifold Pressure Gauge,

Piper PS50031-3 or-4

Encoding Altimeter

Piper PS50008-6 or -7

Engine Hour Meter**

Piper Dwg. 79548-2

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

2.6

* .9

.5 67.2 34 TC 2A13

66 TSOC8b 1.0

2.2

2.6

65.9

67.2

64.4

142

TSOC8b

TSOC4c

64.7 168 TSO C5c

77.6

67.4

TC2A13

TC 2A13

(same as Standard Equipment Weight)

64.7

65.3

66.2

168

TSOC3b

TSO C45

59 TSO C10b

C88

20 TC2A13

*Weight and moment difference between standard and optional equipment.

**Serial nos. 28-7625001 through 28-7625275

REPORT: VB-546 PAGE 5-24

MODEL: PA-28-140

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

CHEROKEE CRUISER

Item Item

J. Autopilots (Optional Equipment)

- - -

- - - - -

- - - - - -

AutoControl III *

Roll Servo

1 C363-1-183R

Console,

1 C338 (thru SIN 9999)

Cables

Attitude Gyro,

52066

Directional Gyro,

520.54

~---

Omni Coupler,

I C388

- - -

--~-

~--

AutoFlite II

Roll Servo,

I C363-1-183R

Cable

Panel Unit,

52075-3 or -4

-_._.-

~--

- - - -

- - - - -

---~.

AutoControl lIIB

**

Roll Servo

1 C363-1-183R

Console,

IC338 (SIN 10000 & up)

Cables

Attitude Gyro,

.52066

Directional Gyro,

.520.54

Omni Coupler,

1 C388

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

2 . .5

1.2

2.3

3.2

122.2

65.1

95.5

64.4

64.0

64.3

2 . .5

2.4

122.2

93.4

64.4

2.5

1.0

2.7

2.9

1.0

122.2

65.1

9.5.5

64.4

64.0

64.3

306 STC SA 1406SW

78 STC SAI406SW

67 STC SAI406SW

148 STC SAI406SW

205 STC SA 1406SW

.58 STC SA 1406SW

306 STC SAI406SW

65 STC SA 1406SW

155 STC SAI406SW

306 STC SAI406SW

65 STC SA 1406SW

48 STC SAI406SW

174 STC SAI406SW

186 STC SAI406SW

64 STC SA1406SW

*Serial nos. 28-7425001 through 28-7425454

**Serial nos. 28-752500 I through 28-7625275

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-25

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

K. Radio Equipment (Optional Equipment)

Narco Mark 16 (VHF Comm/Nav) *

Transceiver, Single

Transceiver, Dual

- -

Narco VOA-50M Omni Converter *

Narco VOA-40(M) Omni Converter *

Narco VOA-40 Omni Converter

Narco Comm lOA VHF

Transceiver

Narco Comm IIA VHF

Transceiver

N arco Dual Comm II A VHF

Transceiver

Narco Nav 10 VHF Receiver

- - -

Narco Nav II VHF Receiver

Narco Nav 12 VHF Receiver

Narco Dual Nav II VHF

Receiver

King KXI70 ( ) VHF Comm/Nav or King KXI75 ( ) VHF Comm/Nav

Transceiver, Single

Transceiver, Dual

King KI201 ( ) VORILOC

Ind.

King Dual KI20 I ( )

VORILOC Ind.

King Kl214 ( ) VOR/LOC/GS

Ind.

*Serial nos. 28-7425001 through 28-7425454

7.5

15.0

2.5

7.1

1.9

2.8

3.4

7.5

15.0

2.1

1.9

3.9

3.6

5.6

5.0

3.2

61.9

64.9

62.4

63.6

64.9

62.4

63.6

61.6

64.9

462

924

TC 2AI3

162 TC 2AI3

324 TC 2AI3

207 TC 2AI3

464

929

136

123

TC 2AI3

243 TC 2AI3

225 TC 2AI3

443

121

178

216

TC 2AI3

TC 2A13

TC 2AI3

356 TC 2AI3

REPORT: VB-546 PAGE 5-26

MODEL: PA-28-140

ISSUED: MAY 14, 1973

REVISED: JULY 13, 1984

Item Item

K. Radio Equipment (Optional

Equipment) (cont)

- - -

Nav Receiving Antenna

Cable, Nav Antenna

- - - -

# I VHF Comm Antenna

- -

Cable, Antenna # I VHF

- - -

#2 VHF Comm Antenna

- - - -

Cable, Antenna # 2 VHF

- - - -

- - -

- - - -

- - - - -

Anti·-Static Kit

# I VHF Comm Antenna

Cable # I VHF Comm Antenna

#2 VHF Comm Antenna

Cable

2 VHF Comm Antenna

Low Frequency Antenna

Static Wicks

. _ - - - -

Narco Audio Panel *

CP-25B/125

- - -

MBT-12-R Marker Beacon

Receiver

Bendix ADFT-12

Receiver

Audio Amplifier

Servo Indicator

Loop Antenna

Cable, Interconnecting

Sense Antenna and Cable

King KR-85 ADF

Receiver

Servo Indicator

Loop Antenna

Loop Cable

Audio Amplifier

Sense Antenna and Cable

* Serial nos. 28-742500 I through 28-7425454

ISSUED: MAY 14, 1973

REVISED: JUNE 13, 1974

CHEROKEE CRUISER

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

265.0

157.0

157.8

105.9

192.8

123.4

1.0

0.4

1.0

0.5

160.8

105.9

195.8

123.4

150.0

1.2 55.0

3.3 75.4

3.5

1.7

1.3

2.3

64.4

57.4

65.9

160.8

108.0

150.0

4.3

1.2

1.3

1.8

64.4

66.3

161.5

108.0

56.0

150.0

133

141

TC 2AI3

161

196

TC 2AI3

TC 2A13

TC 2AI3

66 TC 2AI3

249 TC 2A13

225

112

209

248

TC 2A13

TC 2AI3

TC 2A13

277

210

194

TC 2A13

TC 2AI3

TC 2A13

REPORT: VB-546 PAGE 5-27

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

K. Radio Equipment (Optional

Equipment) (cont)

- - -

UGR-2A Glide Slope

Receiver

Cable

Antenna

Cable, Antenna

- - -

Narco AT-50A Transponder

Panel Unit

- - -

King KN60C DME

Receiver

Antenna

Cable, Antenna

- - - -

King KT76/78 Transponder

Panel Unit

Antenna and Cable

- - -

King KMA-20 ( ) Audio Panel

Antenna

Cable

- -

Piper Automatic Locator

Transmitter, Piper

Dwg 79265-0

Transmitter, Piper

Dwg. 79265-6

Transmitter, Piper

Dwg 79761-3

Antenna and Cable

Shelf and Access Panel

Microphone, Piper Dwg.

68856-10

Microphone (Dynamic)

Piper Dwg. 68856-12

Headset, Piper Dwg.

68856-10

*Weight includes Antenna and Cable.

REPORT: VB-546 PAGE 5-28

MODEL: PA-28-140

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

2.4

1.8

141.8

106.0

92.4

145.0

* 3.0 62.3

6.8

0.3

61.7

112.1

85.6

3.1

1.7

1.3

1.7

.33

63.1

2.8

65.2

116.3

90.0

236.2

224.4

235.4

70.9

65.0

340

191

TC 2A13

TC 2Al3

TC 2AI3

187 TC 2AI3

420

TC 2AI3

196

183

TC 2AI3

TC 2A13

402

307

402

TC 2A13

TC 2AI3

21 TC 2A13

33 TC 2A13

ISSUED: MAY 14,1973

REVISED: JULY 19, 1976

Item Item

K. Radio Equipment (Optional

Equipment) (cont)

- - - -

- - -

King KI-213 VORILOC/GS

Indicator *

King KR-86 ADF

Receiver

Loop Antenna

Loop Cable

Audio Amplifier

Sense Antenna & Cable

King KR-86 ADF (2nd)

Receiver

Loop Antenna

Loop Cable

Sense Antenna & Cable

- -

King KN-73 Glide Slope

Receiver

King KN-77 VORILOC

Converter

King Dual KN-77 VORILOC

Converter

- - -

King KN-65 DME *

Receiver

Antenna

Cable, Antenna

Indicator

King KN-74 R-Nav

Computer

Cable Assy.

King Dual KNI-520

King KN61 DME

King KN65A DME

*Serial nos. 28-7525001 through 28-7625275

ISSUED: JUNE 13, 1974

REVISED: JULY 13, 1984

CHEROKEE CRUISER

Weight

Lbs.

Ann Aft

Datum Moment

Cert.

Basis

2.5 65.4

3.9

1.5

1.3

0.8

0.4

64.4

161.5

108.0

56.0

150.0

3.9

1.5

1.3

3.0

64.4

150.7

105.0

147.5

3.2 184.3

3.6 183.6

7.8 183.6

7.6

0.2

0.3

1.0

201.6

112.1

157.1

67.4

3.7

1.0

5.6

12.5

13.0

62.6

53.0

64.9

179.1

175.2

164 TC 2A13

251

242

140

TC 2A13

251

226

137

443

TC 2A13

TC2A13

TC 2A13

590 TC 2A13

661 TC 2A13

1432 TC 2A13

1532

TC 2A13

TC2A13

232

TC2A13

363 TC 3A13

2239 TC2A13

2278 TSOC66a

REPORT: VB-S46 PAGE S-28a

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

K. Radio Equipment (Optional

Equipment) (cont)

N arco Comm II B VHF

Transceiver *

- - -

Narco Dual Comm II B VHF

Transceiver *

Narco Comm III VHF

Transceiver *

Narco Dual Comm III VHF

Transceiver *

Narco Comm III B VHF

Transceiver *

- -

Narco Dual Comm IIlB VHF

Transceiver *

- -

Narco Nav III VHF Receiver *

- - -

Narco Nav 112 VHF Receiver *

- - -

Narco Nav 14 VHF Receiver *

Narco Nav 114 VHF Receiver *

Narco UGR-3 Glide Slope *

Receiver

Cable

Antenna

Cable, Antenna

Narco CP-I25 Audio Selector

Panel *

Narco ADF-I40*

Receiver

Servo Indicator

Loop Antenna

Cable, Loop

Sense Antenna and Cable

I *Serial nos. 28-7525001 through 28-7625275

REPORT: VB-546 PAGE 5-28b

MODEL: PA-28-140

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

3.9 62.4

7.8

3.0

62.4

6.0

3.9

7.8

2.5

3.3

2.5

62.4

63.6

62.4

2.4

1.8

0.4

0.5

141.8

106.0

92.4

145.0

2.2 55.0

2.5

1.3

1.6

0.6

0.4

63.3

66.0

162.0

105.5

147.5

243 TC 2AI3

487 TC 2A13

187 TC 2AI3

374 TC 2Al3

243 TC 2AI3

487

159

210

156

TC 2AI3

TC 2Al3

340

191

TC 2AI3

TC2Al3

TC 2Al3

TC 2AI3

121 TC 2AI3

158

259

TC 2A13

TC 2AB

TC 2A13

ISSUED: JUNE 13, 1974

REVISED: JULY 13, 1984

Item Item

K. Radio Equipment (Optional

Equipment) (cont)

- - - - -

- -

Narco Dual ADF-140 *

Receivers

Dual Needle Indicator

Loop Antenna # I

Cable, Loop # I

Sense Antenna and Cable

Loop Antenna # 2

Cable, Loop #2

Sense Antenna and Cable

Remote for Dual Ind.

- - -

- -

Narco DME-190*

Receiver

Antenna

Cable, Antenna

- - -

Microphone (Dynamic)*

Piper Dwg. & 68856-11

CHEROKEE CRUISER

Weight

Lbs.

Arm Aft

Datum Moment

Cert.

Basis

5.0

3.5

1.6

0.6

0.4

1.6

0.6

3.0

2.0

5.2

0.3

0.4

0.6

63.3

66.0

162.0

105.5

143.8

150.0

93.8

143.8

185.5

61.8

113.9

85.6

69.9

317

231

259

240

431

371

TC 2AI3

TC 2A13

TC 2AI3

TC 2A13

TC 2AI3

TC 2A13

321

TC 2AI3

42 TC 2A13

*Serial nos. 28-7525001 through 28-7625275

ISSUED: JUNE 13, 1974

REVISED: JULY 13, 1984

REPORT: VB-546 PAGE 5-28c

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-546 PAGE 5-28d

MODEL: PA-28-140

ISSUED: JUNE 13, 1974

CHEROKEE CRUISER

Item Item

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

L. Miscellaneous (Optional Equipment)

- - - -

Fire Extinguisher, Scott

#42211,PiperDwg.76167-2

Brackets - Piper Dwg. 76167

Nose Wheel Fairing,

Piper Dwg. 65348-2

Main Wheel Fairing,

Piper Dwg. 65237

- - - -

Assist Step,

Piper Dwg. 65384-0

- - - -

Lighter

200462

12V Universal

- - - - - -

Jump Seat Installation,

Piper Dwg. 99360-4

Jl1mp Seats (2)

Seat Back 99948-0 (2)

Seat Bottom 99949-0 (2)

.. _ - - - -

Ash Trays (2) 2A20580

Grand Rapids Metalcraft

- - -

Jump Seat Belts and Cables

PS50039-4-3 & 96908-0 & -3

- - - -

Inertia Safety Belts (2)

0.8 Ibs each - PS50039-4-14

Close Out Panel, Piper

Dwg. 66671-0 or-2

Ventilators (2)

Piper Dwg. 68416-1

Assist Strap and Coat Hook

Piper Dwg. 62353-5

Assist Strap

Piper Dwg. 79455

4.6

3.6

7.6

1.8

16.2

*1.1

1.6

*7.3

1.0

71.0

41.3

113.6

156.0

67.9

117.0

110.2

123.0

140.3

140.6

100.9

109.5

.2 109.5

*Weight and moment difference between standard and optional equipment.

327

149

863

281

1895

135

224

1026

101

TC 2A13

TC 2AI3

TC 2A13

ISSUED: MAY 14, 1973

REVISED: JUNE 13, 1974

REPORT: VB-546 PAGE 5-29

MODEL: PA-28-140

CHEROKEE CRUISER

Item Item

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

L. Miscellaneous (Optional

Equipment) (cont)

- - - -

Vert. Adjustable Front Seat

(Left), Piper Dwg. 79180-0

(Left), Piper Dwg. 79590-0

- - -

Vert. Adjustable Front Seat

(Right), Piper Dwg. 79180-1

(Right), Piper Dwg. 79590-1

Cabin Overhead Vent System

Piper Dwg. 79183-0 6,

- - -

Cabin Overhead Vent System

With Ground Ventilating Blower

Piper Dwg. 79183-26

Cabin Overhead Vent System

Piper Dwg. 79183-3 6,

Cabin Overhead Vent System

With Ground Ventilating Blower

Piper Dwg. 79183-4 6,

Super Cabin Sound Proofing

Piper Dwg. 78030-0

Alternate Static Source

Calibrated Alternate Static Source

Placard Required: Yes No

Headrest (2) (Front) Piper

Dwg. 96806-17 or 79337-18

Air Conditioning Installation

Piper Dwg. 99286-3 6

Zinc Chromate Finish

6.6

5.0

6.8

5.1

12.6

5.6

13.1

16.3

2.0

67.0

5.0

85.2

84.8

84.6

84.2

159.2

171.8

159.8

171.4

89.3

66.0

99.5

107.5

158.0

Corrosive Resistant Kit 3.0 106.0

Weight and moment difference between standard and optional equipment.

6 Requires optional close out panel.

562

424

575

429

812

2165

893

2246

1456

199

7203

790

318

TC 2A13

REPORT: VB-546 PAGE 5-30

MODEL: PA-28-140

ISSUED: MAY 14,1973

REVISED: MAY 16, 1975

Item Item

L. Miscellaneous (Optional

Equipment) (cont)

Stainless Steel Control Cables

CHEROKEE CRUISER

Weight Arm Aft

Lbs. Datum Moment

Cert.

Basis

TC 2AD

TOTAL OPTIONAL EQUIPMENT

EXTERIOR FINISH

Base Color

Accent Color

ISSUED: MAY 14, 1973

REVISED: MAY 16, 1975

REPORT: VB-546 PAGE 5-31

MODEL: PA-28-140

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT' BLANK

REPORT: VB-546 PAGE 5-32

MODEL: PA-28-140

ISSUED: MAY 14, 1973

LOADING INSTRUCTIONS

THIS SECTION IS NOT

APPLICABLE TO THIS AIRPLANE

6-i

-<:.

OPERATING

I~STRUGTIONS

,',

Preflight .......................................................................................................................................... 7-1

Starting Engine .............................................................................................................................. .

Starting Engine When Cold .................................................................................................... .

Starting Engine When Hot ..................................................................................................... .

Starting Engine When Flooded ....................... ~ ...................................................................... .

7-2

Starting Engine With External Power Source ........................................................................ .

Warm-Up ....................................................................................................................................... .

Ground Check ................................................................................................................................ .

Takeoff ........................................................................................................................................... .

Climb ............................................................................................................................................. .

Stalls .............................................................................................................................................. .

Cruising ......................................................................................................................................... .

Turbulent Air Operation ................................................................................................................ .

7-2

7-3

7-4

7-5

7-6

Maneuvers ..................................................................................................................................... .

Approach and Landing .................................................................................................................. .

Stopping Engine ............................................................................................................................ .

Airspeed Data ..................................................................... ,' .......................................................... .

Mooring ......................................................................................................................................... .

Weight and Balance ....................................................................................................................... .

Air Conditioning ............................................................................................................................ .

Air Conditioner Operational Check Procedure ............................................................................. .

Air Conditioner Effects on Airplane Performance ........................................................................ .

Emergency Locator Transmitter .................................................................................................... .

7-9

7-10

7-6

7-7

7-8

7-i

CHEROKEE CRUISER

OPERA TlNG INSTRUCTIONS

PREFLIGHT

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

I. a. Release seat belt securing control wheel. b. Master switch OK c. Check fuel quantity indicators (two tanks). d. Master switch and ignition OFF.

2. a. Check for external damage, operation 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 caps. b. Drain all fuel system sumps and lines and check for water, sediment and proper fuel. (See Fuel System Section for procedure.) c. Check that fuel system vents are open.

4. a. Check landing gear shock struts for proper inflation (approximately 4-1/2 inches). b. Check tires for cuts, wear and proper inflation. c. Check brake blocks and discs for wear and damage.

1----t-----2-----~----1

.,.

I i--t-~I

I r---~-------2----~,--~----2-------~---,

, I

I .. 3

~--~-------4----t-~

I ..

...

I "'-"'--5---.-"

I r-t----4--------t-J

OPERATING INSTRUCTIONS

REVISED: JULY 13, 1984

7-1

CHEROKEE CRUISER

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 maximum (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 (approximately 3-114 inches). h. Check for foreign matter in air inlets.

Check alternator belt tension.

6. a. Stow tow bar and control locks, if used. b. Check baggage for proper storage and security.

7. a. Upon entering aircraft ascertain that all primary flight controls operate properly. b. Close and secure the cabin door. c. Check that required papers are in order and in the aircraft. d. Fasten seat belts and shoulder harness. Check function of inertia reel.

STARTING ENGINE

1. Set parking brake ON.

2. Set the carburetor heat control in the full COLD (OFF) position.

3. Select the desired tank with fuel selector valve.

STARTING ENGINE WHEN COLD

1. Open throttle approximately 114 inch.

2. Turn the master switch ON.

3. Turn the electric fuel pump ON.

4. Move the mixture control to FULL RICH.

5. Engage the starter by rotating magneto switch clockwise and pressing in.

6. When the engine fires, advance throttle to desired setting. If the engine does not fire within five to ten seconds, disengage starter and prime with one to three strokes of the priming pump. Repeat starting procedure.

STARTING ENGINE WHEN HOT

1. Open the throttle approximately 112 inch.

2. Turn the master switch ON.

3. Turn the electric fuel pump ON.

4. Put mixture control in full RICH.

5. Engage the starter by rotating magneto switch clockwise and pressing in. When the engine fires move the throttle to desired setting.

STARTING ENGINE WHEN FLOODED

1. Open the throttle full.

2. Turn the master switch ON.

3. Turn the electric fuel pump OFF.

7-2

OPERATING INSTRUCTIONS

REVISED: JUNE 3,1977

CHEROKEE CRUISER

4. Put mixture control in IDLE CUT-OFF.

5. Engage the starter by rotating magneto switch clockwise and pressing in. When the engine fires, advance the mixture control and retard the throttle.

When the engine is firing evenly, advance the throttle to 800 RPM. If oil pressure is not indicated within thirty seconds, stop the engine and determine the trouble. In cold weather it will take a few seconds longer to get an oil pressure indication. If the engine has failed to start, refer to the "Lycoming Operating Handbook, Engine Troubles and Their Remedies."

Starter manufacturers recommend that cranking periods be limited to thirty seconds with a two minute rest between cranking periods. Longer cranking periods will shorten the life of the starter.

STARTING ENGINE WITH EXTERNAL POWER SOURCE*

An optional feature known as Piper External Power (PEP) allows the operator to use an external battery to crank the engine without having to gain access to the aircraft battery.

The procedure is as follows:

1. Turn aircraft MASTER SWITCH to OFF.

2. Connect RED lead of PEP kit jumper cable to POSITIVE (+) terminal of external 12-volt battery and BLACK lead to NEGATIVE (-) terminal.

3. Insert plug of jumper cable into socket located on aircraft fuselage.

4. Turn aircraft MASTER SWITCH to ON and proceed with NORMAL engine starting technique.

5. After engine has been started, turn MASTER SWITCH to OFF and remove jumper cable plug from aircraft.

6. Turn aircraft MASTER SWITCH to ON and check alternator ammeter for indication of output. DO NOT ATTEMPT FLIGHT IF THERE IS NO

INDICATION OF ALTERNATOR OUTPUT.

WARM-UP

As soon as the engine starts, the oil pressure should be checked. If no pressure is indicated within thirty seconds, stop the engine and determine the trouble. In cold weather it will take a few seconds longer to get an oil pressure indication. Warm-up the engine at 800 to 1200 RPM.

Takeoff may be made as soon as the ground check is completed, providing that the throttle may be opened fully without backfiring, or skipping, and without a reduction in engine oil pressure.

GROUND CHECK

Check the magnetos at 2000 RPM by switching from Both to Right then back to Both before switching to Left. Differential drop should not exceed 50 RPM while the total drop on either magneto should not exceed 175 RPM.

Check vacuum gauge; indicator should read 5" ± .1" Hg at 2000 RPM.

* Optional equipment

OPERATING INSTRUCTIONS

ISSUED: JULY 6, 1973 7-3

CHEROKEE CRUISER

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 takeoff.

Check the annunciator panel lights with the press-to-test button*.

Carburetor heat should also be checked prior to takeoff to be sure that the control is operating properly and to clear any ice which may have formed during taxiing. Avoid prolonged ground operation with carburetor heat ON as the air is unfiltered.

Operation of the engine driven fuel pump should be checked while taxiing or during preflight engine run up by switching off the electric fuel pump and observing fuel pressure. The electric fuel pump should be on during takeoff to prevent loss of power should the engine driven pump fail. The engine is warm enough for takeoff when the throttle can be opened without the engine faltering. For air conditioner ground check refer to page 7-8.

TAKEOFF

Just before takeoff the following items should be checked:

1. Fuel on proper tank

2. Electric fuel pump - on

3. Engine gauges - checked

4. Flaps - set

5. Carburetor heat - off

6. Mixture - set

7. Seat backs - erect

8. Safety Belts/harness - fastened

9. Empty seats- seat belts snugly fastened

10. Trim tab - set

11. Controls - free

12. Door -latched

13. Air conditioner - off

NOTE

Mixture full rich except a minimum amount of leaning is permitted for smooth engine operation when taking off at high elevation.

In the conventional takeoff procedure set the trim control slightly aft of neutral. Allow the airplane to accelerate to 50 to 60 miles per hour, then ease back on the wheel enough to let the airplane fly itself from the ground. Premature or excessive raising of the nose will result in a delayed takeoff. After takeoff let the aircraft accelerate to the desired climb speed by lowering the nose slightly.

Short Field, Obstacle Clearance:

Lower the flaps to 25 0 (second notch), accelerate to 55-60 miles per hour and ease back on the control wheel to rotate. After breaking ground, accelerate to the best angle of climb speed,

78 miles per hour. Slowly retract the flaps when the obstacle has been cleared, and continue climb at 89 miles per hour.

Short Field, No Obstacles:

Lower the flaps to 25

(second notch), accelerate to 55-60 miles per hour. Ease back on the control wheel to rotate and accelerate to best rate of climb speed, 89 miles per hour. Slowly retract the flaps while climbing out.

*Serial nos. 28-7525001 through 28-7625275

7-4

OPERATING INSTRUCTIONS

REVISED: JULY 13, 1984

CHEROKEE CRUISER

Soft Field, No Obstacle:

Lower the flaps to 25° (second notch), accelerate aircraft and pull nose gear from the ground as soon as possible, lift off at lowest possible airspeed. Accelerate just above the ground to best rate of climb speed, 89 miles per hour. Climb out while slowly retracting the flaps.

Soft Field, Obstacle Clearance:

Lower flaps to 25° (second notch), accelerate aircraft, pull nose gear off as soon as possible and lift off at lowest possible airspeed. Accelerate just above the ground to best angle of climb speed, 78 miles per hour to climb past obstacle clearance height; continue climb while accelerating to best rate of climb speed, 89 miles per hour, and slowly retract the flaps.

CLIMB

The best rate of climb airspeed at gross weight is 89 miles per hour. The best angle of climb airspeed is 78 miles per hour. At lighter than gross weight these speeds are reduced. The recommended en route climbing speed of 100 miles per hour provides increased visibility over the nose. Shallow turns of a few degrees will also aid forward visibility during climb out. The air conditioner may be turned on after all obstacles have been cleared.

STALLS

Stall characteristics of the Cherokee are conventional. Visual stall warning is provided by a red light located on the left side of the instrument panel which illuminates automatically between 5 and 10 miles per hour above stall speed. Gross weight stalling speed with power off and full flaps is 55 miles per hour at 2150 pounds. With flaps up this speed is increased 9 miles per hour. Loss of altitude during stalls can be as great as 200 feet, depending on configuration and power. Intentional spins are prohibited in the normal category airplane and when air conditioning or ventilation blower is installed.

CRUISING

The cruising speed 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 Performance Charts Section.

Use of the mixture control in cruising flight reduces fuel consumption significantly, especially at higher altitudes, and reduces lead deposits when the alternate fuels are used. The mixture should be leaned when 75% power or less is being used. If any doubt exists as to the amount of power being used, the mixture should be in the FULL RICH position for all operations. Always enrich the mixture before increasing power settings.

To lean the mixture, pull the mixture control until the engine becomes rough, indicating that the lean mixture limit has been reached in the leaner cylinders. Then enrich the mixture by pushing the control towards the instrument panel until engine operation becomes smooth.

OPERATING INSTRUCTIONS

REVISED: APRIL 19, 1976 7-5

CHEROKEE CRUISER

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 cruising flight, the fuel should be used alternately from each main 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.

TURBULENT AIR OPERATION

In keeping with good operating practice used in all aircraft, it is recommended that when turbulent air is encountered or expected the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build-ups which may occur as a result of the turbulence or distractions caused by the conditions.

MANEUVERS

The airplane is approved for certain aerobatic maneuvers, provided it is loaded within the approved weight and center of gravity limits. (See Airplane Flight Manual.) The maneuvers are spins, steep turns, lazy eights and chandelles. Spins are prohibited when air conditioning is installed.

Intentional spins are prohibited in the normal category airplane. Lazy eights and chandelles may be performed in the normal category provided a 60° angle of bank and/or a 30° angle of pitch is not exceeded. For approved maneuvers and entry speed refer to the Airplane Flight

Manual.

APPROACH AND LANDING

Landing check list:

1. Fuel on proper tank

2. Mixture - full rich

3. Electric fuel pump on

4. Seat backs - erect

5. Flaps - set (115 MPH)

6. Safety Belts/harness - fastened

7. Air conditioner - off

The airplane should be trimmed to an approach speed of about 85 miles per hour with flaps up. The flaps can be lowered at speeds up to 115 miles per hour, approach speed is reduced 3 miles per hour for each notch of flaps used. 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 carburetor 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 is generally good practice to contact the ground at the minimum possible safe speed consistent with existing conditions.

7-6

OPERATING INSTRUCTIONS

REVISED: APRIL 19, 1976

CHEROKEE CRUISER

Normally, the best technique for short and slow landings is to use full flaps 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. 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.

STOPPING ENGINE

At the pilot's discretion, the flaps should be raised and the electric fuel pump turned off.

After parking, the air conditioner and radios should be turned off and the engine stopped by pulling the mixture control to idle cut-off. The throttle should be left full aft to avoid engine vibration while stopping. Then the magneto and master switches should be turned off and the parking brake set.

AIRSPEED DATA

All airspeeds quoted in this manual are calibrated unless otherwise noted. Calibrated airspeed is indicated airspeed corrected for instrument and position errors. The following table gives the correlation between indicated airspeed and calibrated airspeed if zero instrument error is assumed. This calibration is valid only when flown at maximum gross weight in level flight.

AIRSPEED CORRECTION TABLE

Flaps 0° lAS-MPH

CAS - MPH

100

101

110

120

119

130

128

140 150

137 146

Flaps 40° lAS - MPH

CAS-MPH

100

110

108

120

117

OPERATING INSTRUCTIONS

REVISED: JUNE 13, 1974 7-7

CHEROKEE CRUISER

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 seat belt through the control wheel and pulling it snug. 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 in flight. For weight and balance data see the Airplane Flight Manual and Weight and Balance form supplied with each airplane.

AIR CONDITIONING*

To operate the air conditioning system either on the ground or in flight:

1. Start the engine (ground operation).

2. Turn the air conditioning Master Switch to "ON."

3. Turn "TEMP" control to desired temperature. Clockwise rotation increases cooling.

4. Select desired "FAN" position, "LOW," "MED" or "HIGH."

AIR CONDITIONER OPERATIONAL CHECK PROCEDURE

Prior to takeoff the air conditioner should be checked for proper operation as follows:

1. Check aircraft Master Switch ON.

2. Select desired "FAN" position, "LOW," "MED" or "HIGH."

3. Turn the air conditioner control switch to "ON" - the "Air Condo Door Open" warning light will turn on, thereby indicating proper air conditioner condenser door actuation.

4. Turn the air conditioner control switch to "OFF" - the "Air Condo Door Open" warning light will go out, thereby indicating the air conditioner condenser door is in the up position.

5. If the "Air Condo Door Open" light does not respond as specified above, an air conditioner system or indicator bulb malfunction is indicated, and further investigation should be conducted prior to flight.

The above operational check may be performed during flight if an inflight failure is suspected.

Optional equipment

7-8

OPERATING INSTRUCTIONS

ISSUED: JULY 6, 1973

CHEROKEE CRUISER

Air Conditioner Controls

AIR CONDITIONER EFFECTS ON AIRPLANE PERFORMANCE

Operation of the air conditioner will cause slight decreases in the cruise speed and range of the Cherokee 140. Power from the engine is required to run the compressor, and the condenser door, when extended, causes a slight increase in drag. When the air conditioner is turned off there is normally no measurable difference in climb, cruise or range performance of the airplane.

NOTE

To insure maximum climb performance the air conditioner must be turned off manually before takeoff to disengage the compressor and retract the condenser door. Also the air conditioner must be turned off manually before the landing approach in preparation for a possible go-around.

Although the cruise speed and range are only slightly affected by the air conditioner operation, these changes should be considered in preflight planning. To be conservative, the following figures assume that the compressor is operating continuously while the airplane is airborne. This will be the case only in extremely hot weather.

OPERATING INSTRUCTIONS

ISSUED: JULY 6,1973 7-9

CHEROKEE CRUISER

I. The decrease in true airspeed is approximately 5 mph at 75% power and 4 mph at

50% power.

2. The decrease in range may be as much as 28 statute miles for the 36 gal. (standard) capacity and as much as 39 statute miles for the 50 gal. (reserve) capacity.

NOTE

To read power from the Power vs. Density Altitude Chart in this manual, add 50 rpm to the value observed on the tachometer when the air conditioner is operating.

The climb performance of Cherokee 140 is not compromised measurably with the air conditioner operating since the compressor is dec1utched and the condenser door is retracted, both automatically, when a full throttle position is selected. When the full throttle position is not used or in the event of a malfunction which would cause the compressor to operate and the condenser door to be extended, a decrease in rate of climb of as much as 100 fpm can be expected. Should a malfunction occur which prevents condenser door retraction when the compressor is turned off, a decrease in rate of climb of as much as 50 fpm can be expected.

EMERGENCY LOCATOR TRANSMITTER*

The Emergency Locator Transmitter (ELT) when installed, is located in the aft portion of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage. (On aircraft manufactured prior to mid-1975, this plate is retained by three steel Phillips head screws. On aircraft manufactured from mid-1975 and on, this plate is attached with three slotted-head nylon screws for ease of removal; these screws may be readily removed with a variety of common items such as a dime, a key, a knife blade, etc. If there are no tools available in an emergency the screw heads may be broken off by any means.) The ELT is an emergency locator transmitter which meets the requirements of FAR 91.52. The unit operates on a self-contained battery.

A battery replacement date is marked on the transmitter label. To comply with FAA regulations, the battery must be replaced on or before this date. The battery must also be replaced if the transmitter has been used in an emergency situation or if the accumulated test time exceeds one hour, or if the unit has been inadvertently activated for an undetermined time period.

On the unit itself is a three position selector switch labeled "OFF," "ARM" and "ON."

The "ARM" position is provided to set the unit to the automatic position so that it will transmit only after impact and will continue to transmit until the battery is drained to depletion or until the switch is manually moved to the "OFF" position. The "ARM" position is selected when the transmitter is installed at the factory and the switch should remain in that position whenever the unit is installed in the airplane. The "ON" position is provided so the unit can be used as a portable transmitter or in the event the automatic feature was not triggered by impact or to periodically test the function of the transmitter.

Select the "OFF". position when changing the battery, when rearming the unit if it has been activated for any reason, or to discontinue transmission.

Optional equipment

7-10

OPERATING INSTRUCTIONS

REVISED: APRIL 16, 1979

CHEROKEE CRUISER

NOTE

If the switch has been placed in the "ON" posItIon for any reason, the "OFF" position has to be selected before selecting

"ARM." If "ARM" is selected directly from the "ON" position, the unit will continue to transmit in the "ARM" position.

A pilot's remote switch, located on the left side panel, is provided to allow the transmitter to be controlled from inside the cabin.

1. On some models the pilot's remote switch has three positions and is placarded "ON,"

"AUTO/ARM," and "OFF/RESET." The switch is normally left in the

"AUTO/ARM" position. To turn the transmitter off, move the switch momentarily to the "OFF/RESET" position. The aircraft master switch must be "ON" to turn the transmitter "OFF." To activate the transmitter for tests or other reasons, move the switch upward to the "ON" position and leave it in that position as long as transmission is desired.

2. On other models the pilot's remote switch has two positions and is placarded

"ON/RESET" and "ARM (NORMAL POSITION)." The switch is normally left in the down or "ARM" position. To turn the transmitter off, move the switch to the

"ON/RESET" position for one second then return it to the "ARM" position. To activate the transmitter for tests or other reasons, move the switch upward to the

"ON/RESET" position and leave it in that position as long as transmission is desired.

The locator should be checked during the ground check to make certain the unit has not been accidentally activated. Check by tuning a radio receiver to 121.5 MHz. If there is an oscillating sound, the locator may have been activated and should be turned off immediately.

Reset to the "ARM" position and check again to insure against outside interference.

NOTE

If for any reason a test transmission is necessary, the test transmission should be conducted only in the first five minutes of any hour and limited to three audio sweeps. If tests must be made at any other time, the tests should be coordinated with the nearest FAA tower or flight service station.

OPERATING INSTRUCTIONS

REVISED: JUNE 3, 1977 7-11

OPERATING TIPS

Operating Tips ........................................................................................................................... 8-\

8-i

CHEROKEE CRUISER

OPERATING TIPS

The following Operating Tips are of particular value in the operation of the Cherokee 140.

1. Learn to trim for takeoff so that only a very light back pressure on the wheel is required to lift the airplane off the ground.

2. The best speed for takeoff is about 60 MPH under normal conditions. Trying to pull the airplane off the ground at too low an airspeed decreases the controllability of the airplane in event of engine failure.

3. Flaps may be lowered at airspeeds up to 115 MPH. To reduce flap operating loads, it is desirable to have the airplane at a slower speed before extending the flaps.

4. Before attempting to reset any circuit breaker, allow a two to five minute cooling off period.

5. Before starting the engine, check that all radio switches, light switches and the pitot heat switch are in the off position so as not to create an overloaded condition when the starter is engaged.

6. The overvoltage relay is provided to protect the electronics equipment from a momentary overvoltage condition (approximately 16.5 volts and up), or a catastrophic regulator failure. In the event of a momentary condition, the relay will open and the ammeter will indicate "0" output from the alternator. The relay may be reset by switching the ALT switch to OFF for approximately 1 second and then returning the ALT switch to ON. If after recycling the ALT switch the condition persists, the flight should be terminated as soon as practical; reduce the battery load to a minimum. The ALT light on the annunciator panel* will illuminate if the alternator fails. Recycle the ALT switch and check the ALT FIELD circuit breaker. If the failure persists after this action, reduce electrical loads and land as soon as practical,

7. The vacuum gauge is provided to monitor the pressure available to assure the correct operating speed of the vacuum driven gyroscopic flight instruments. It also monitors the condition of the common air filter by measuring the flow of air through the filter.

If the vacuum gauge does not register 5"

±

.10" Hg at 2000 RPM, the following items should be checked before flight: a. Common air filter could be dirty or restricted. b. Vacuum lines could be collapsed or broken. c. Vacuum pump worn. d. Vacuum regulator, not adjusted correctly. The pressure, even though set correctly, can read lower under two conditions: (1) Very high altitude, above 12,000 feet, (2) Low engine RPM, usually on approach or during training maneuvers. This is normal and should not be considered a malfunction.

Serial nos. 28-7525001 through 28-7625275

OPERATING TIPS

REVISED: JULY 13, 1984 8-1

CHEROKEE CRUISER

8. The shape of the wing fuel tanks is such that in certain maneuvers the fuel may move away from the tank outlet. If the outlet is uncovered, the fuel flow will be interrupted and a temporary loss of power may result. Pilots can prevent inadvertent uncovering of the outlet by avoiding maneuvers which could result in uncovering the outlet.

Extreme running turning takeoffs should be avoided as fuel flow interruption may occur.

Prolonged slips or skids which result in excess of 2000 feet of altitude loss, or other radical or extreme maneuvers which could cause uncovering of the fuel outlet must be avoided as fuel flow interruption may occur when tank being used is not full.

9. Anti-collision lights should not be operating when flying through overcast and clouds, since reflected light can produce spacial disorientation. Do not operate strobe lights when taxiing in the vicinity of other aircraft.

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

11. In an effort to avoid accidents, pilots should obtain and study the safety related information made available in FAA publications such as regulations, advisory circulars, Aviation News, AIM and safety aids.

12. During letdown and low power flight operations, it may be necessary to lean because of excessively rich mixture. Always go to full rich prior to landing sequence.

13. When leaning, careful observation of the temperature instruments should be practiced.

14. When alternate fuels are used, the engine should be run up to 1200 RPM for one minute prior to shutdown to clean out any unburned fuel.

8-2

OPERATING TIPS

REVISED: APRIL 19, 1976

PERFORMANCE CHARTS

Altitude Conversion Chart.............................................................................................................. 9-1

Takeoff Performance ...................................................................................................................... 9-2

Climb Performance......................................................................................................................... 9-3

Engine Performance .... .......... ........ ....... .......... ... .......... ..... .......... ........ .... ........ ............................ .... 9-4

Cruise Performance - True Airspeed .............................................................................................. 9-5

Cruise Performance - Range (Standard Fuel Capacity).................................................................. 9-6

Cruise Performance - Range (Maximum Fuel Capacity) ............................................................... 9-7

Glide Performance .......................................................................................................................... 9-8

Stall Speed vs Aircraft Gross Weight ............................................................................................. 9-9

Stall Speed vs Angle of Bank ......................................................................................................... 9-10

Landing Performance .... ............... ....... ...... ....... ...... .......... ..... ... .............. ......... ......................... ...... 9-11

WARNING

PERFORMANCE INFORMATION DERIVED BY EXTRAPO-

LATION BEYOND THE LIMITS SHOWN ON THE CHARTS

SHOULD NOT BE USED FOR FLIGHT PLANNING PURPOSES.

9-i

CHEROKEE CRUISER

PA-28-140

CHEROKEE

I

I I I

I I

I I I I ti\~ trutrlW@~ ~@~W~OO$U@rro ~[}{]ti\ootr

THIS CHART SHOULD BE USED TO

DETERMINE DENSITY ALTITUDE

FROM EXISTING TEMPERATURE

AND PRESSURE ALTITUDE CONDITIONS

FOR USE WITH PERFORMANCE CHARTS.

24000

20000

E

!::i

>t::

CI') z:

....,

12000

8000

4000

·40

.......-

f4-

1 - -

V"'"

..............

".-

STD.

TEMP. '\

----

.--'

........-

.."..... ......

..".....

V ,.,. \

-r

.t-

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~¢

.---

I--"'

\I~

----

I---

----

V-

--l,..---

~~~

L--

,..-

---

".-

~ o ·20 20 40 60 80 100

TEMPERATURE.

PERFORMANCE CHARTS

ISSUED: JULY 6, 1973 9-1

CHEROKEE CRUISER

9-2

PA-28-140

CHEROKEE

I

7000

6000

5000

....

.... c=a c=a

i=

i= c

....

...

4000

3000

2000

1000

II)

II) lit

...

to-

... o

500

FLAPS 0°

PAVED LEVEL DRY RUNWAY

FULL POWER BEFORE BRAKE RELEASE

ZERO WIND

EXTRAPOLATION OF CHART ABOVE 7000 FT. IS ItVAUO-

I - iii

;1 ill

/ '

/ /

t

1 il

GROSS WEIGHT

1950

--- 2150

LBS.

, r

/

/ /

/ V

~/ /

I,' /

/ /

I /

1// / /

AIRSPEED THROUGH 50 FEET

1950 LBS •• 72 MPH CAS

2150 LBS .• 76 MPH CAS

I - -

4000 1000 1500 2000 2500 3000 3500

TAKE OFF DISTANCE • FEET

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

PERFORMANCE CHART

REVISED: JUNE 13, 1974

CHEROKEE CRUISER

PA-28-140

CHEROKEE

1 1 1 I [ I

~~O~[;) [f)[g~~@~~~~~[g

II>

...

TAKEOFF GROSS WEIGHT 2150 LBS.

FLAPS

0°

POWER • FUll THROTTlE

MIXTURE· LEAN PER LYCOMING INSTRUCTIONS

89 MPH CAS

14000

12000

10000

\ t:; 1000

.....

.

~ c::a i=

S c

10 DO

I:

=-= c::a 4000

\ f\

2000

211 400 f\

,

600 100

RA

OF

CUIB·FEET

PER

IllITE

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974 9-3

CHEROKEE CRUISER

II)

,...

PA-28-140

CHEROKEE

GROSS WEIGHT 2150 LBS.

WHEEL FAIRINGS INSTALLED

MIXTURE· LEAN PER LYCOMING INSTRUCTIONS

BEST POWER

14000

9-4

12000

10000

...

.... c:a

....

--I

....

.... c:a

8000

6000

4000

2000 o

2000 2100

:::

/ j

~ f fJ

I ~o

~

/ ~-

A r

V i

/

2200 2300 2400 2500 2600

ENGINE R. P. M.

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

2700

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974

CHEROKEE CRUISER tit tit tit

... po.

PA-28-140

CHEROKEE

~~Mo~rn ~rn~~@~~I~~~rn

Q lr~M~ ~o~i~rn~@-

GROSS WEIGHT 2150 LBS.

NO WHEEL FAIRINGS INSTALLED

BEST POWER

MIXTURE • LEAN PER LYCOMING INSTRUCTIONS

14000

....

12000

.... c:a e

!:; c

10000 c:;; z

~ 8000

6000

4000

2000 o

100

.... / r-

FUll THROTILE

NOTE: ADD 3 MPH WHEN WHEEL -

'I'

FAIRINGS ARE INSTALLED.

Q..

/ \

\ I

II .I I~

EI ~

I i

~ j

I ff

::J

/ ~I \

V L

I /

140 110 120 130 150 160

TRUE AIRSPEED. M.P.H.

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974 9-5

CHEROKEE CRUISER

9-6

PA-28-140

!:i

-c

>t::

""

SOOO

4000

...

CHEROKEE

I I I I I I I I

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14000 ,....---

12000

GROSS WEIGHT 2150 LBS.

WHEEL FAIRINGS INSTALLED

ST ANDARD FUEL CAPACITY 36 GAL.

34 GAL. USABLE FUEL

BEST ECONOMY

MIXTURE • LEAN PER LYCOMING INSTRUCTIONS

I I

ZERO WIND

NO RESERVE

---

45 MIN. RESERVE AT 55% POWER

:gl

. "

10000

2000 ri

...

..... c:o

....

•

.,,'

' .... co

..........

: k!

I I, I

II t;

I 1/

APPROX.

GPH

8.4

7.3

S.2 o

300

PERCENT

RATED

POWER

400 500 600 700 800 r----

' - - -

-t--

RANGE·STATUTE MILES

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974

14000

12000

10000

1.10..

Q =

!::

I -

--'

>l v;

....,

BODO

6000

4000

2000

II>

...

"

i o

400

CHEROKEE CRUISER

PA-28-140

CHEROKEE

I I I I I I I I ct:[;3M~~~ [P~rF3~@OO[M~[M~~

I I rF3~[M@~

GROSS WEIGHT 2150 LBS.

WHEEL FAIRINGS INSTALLED

MAXIMUM FUEL CAPACITY 50 GAL.

48 GAL. USABLE FUEL

BEST ECONOMY

MIXTURE· LEAN PER LYCOMING INSTRUCTIONS

ZERO WIND

I I I

- - NO RESERVE

- - - 45 MIN. RESERVE AT 55% POWER t---

500

Q" e

<:::)

te

,.,;;;

/i;- .....

';"

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I II

II ~

,'/

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III

,

....

('/

//

....

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''':' l;a

1 i

1/

PERCENT

RATED

POWER

600 100 BOO 900

RANGE·STATUTE MILES

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

t - - -

APPROX.

GPH

8.4

1.3

6.2

I I

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974 9-7

CHEROKEE CRUISER

...

PA-28-140

CHEROKEE

J I I 1 I I I

@[L~@~ [f)~OO~@OO[Mti\[ro~~

GROSS WEIGHT 2150 LBS.

PROP WINDMILLING

FLAPS 0

ZERO WIND

STANDARD DAY CONDITIONS

85 MPH CAS

14000

.....

12000

:!: c

....,

!;!

C) act

10000

....,

i=

..... c

BODO

6000

4000

2000

S.l.

. o

V jV

/

10 15

V jV

20 25

GLIDE DISTANCE· STATUTE MILES

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974 9-8

... lit lit

,...

PA-28-140

CHEROKEE

I I I I I

Wrs

~~!ru~~~~V

@!ru@~~ wrn~@[g]lf

POWER OFF

CHEROKEE CRUISER

80 en c u

::c

Q., =-

.....

Q., en

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I en

....-

.---

~4)~~\\ ~

~v\)O ~

.., V

1400 1600 1800 2000 2200

AIRCRAR GROSS WEIGHT . POUNDS

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

PERFORMANCE CHARTS

REVISED: JUNE 13,1974 9-9

CHEROKEE CRUISER

...

PA-28-140

CHEROKEE

J J r

$11 ~!L!L $[P~~[p)

~OO@Il~ @[f OO~OO[16

GROSS WEIGHT - 2150 LIS.

POWER OFF

100

90

80

:z:

:IE

Q ....

A. en

70

c .... en

60

50 f\.~'S$-

' /

/

---i

9-10

40

20

40 ANGLE OF BANK - DEGREES

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

60

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974

CHEROKEE CRUISER on on on -

PA-28-140

CHEROKEE

I I I I I I I

[!.~[ro@a[ro@ ~~OO~@OO[AA)~[ro({:~

GROSS WEIGHT 2150 lBS.

PAVED LEVEL DRY RUNWAY

POWER OFF

40° FLAPS

ZERO WIND

MAXIMUM BRAKING

APPROACH AIRSPEED 71 MPH CAS

7000

....

IDOl

5000

4000

3000

I

CII

2000

100. o , ... I

20. 40. 101 •••

WlDItC DlSTlJICE, FEET

NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING

INSTALLATION ON PERFORMANCE.

1201 lUI

PERFORMANCE CHARTS

REVISED: JUNE 13, 1974 9-11

HANDLING AND SERVICING

Ground Handling ..................... ........... .............. ........ ......... ................ ..... ........................................ 10-1

Towing .. ....... ........... ............. ....... ....... ........... ....... ..................... .................... .................... 10-1

Taxiing .............................................................................................................................. 10-1

Parking .............................................................................................................................. 10-2

Mooring .............................................................................................................................. 10-2

Cleaning .............................................................................................................................. 10-3

Cleaning Engine Compartment .............................................................................................. 10-3

Cleaning Landing Gear .......................................................................................................... 10-3

Cleaning Exterior Surfaces..................................................................................................... 10-4

Cleaning Windshield and Windows ............ ............ .......................................................... ..... 10-4

Cleaning Headliner, Side Panels and Seats ............................................................................ 10-5

Cleaning Carpets .... ........... ......... ... .............. ......... ..... ........ .......... ..... .............. .................... .... 10-5

Power Plant Induction Air Filter .................................................................................................... 10-5

Removal of Induction Air Filter ............................................................................................. 10-5

Cleaning Induction Air Filter ................................................................................................. 10-5

Installation of Induction Air Filter ......................................................................................... 10-5

Brake Service ... ............. ....... .................. ...... ..... ........... ............... ........... .......... ............... ............ 10-7

Landing Gear Service ....... ........ ................. .......... ........... ........................... ............ ............ ............. 10-7

Propeller Service. .... ........ ........ .................. ........ .......... ............... ... ...... ........................ .................... 10-8

Oil Requirelnents ............................................................................................................................ 10-8

Fuel System .............................................................................................................................. 10-8

Fuel Requirements.................................................................................................................. 10-8

Filling Fuel Tanks................................................................................................................... 10-9

Draining Fuel Valves and Lines ............................................................................................. 10-10

Draining Fuel System ..... .......... ........ ....... ..... .............. ................................. ........................... 10-10

Tire Inflation . ....... ......... ............... ..... ............... ........... ............................................... ................ 10-10

Battery Service ........ ............ ............... .......... ............. ....... ............. ........... ..................... ................ 10-10

Facts You Should Know ................................................................................................................. 10-11

Preventive Maintenance ................................................................................................................. 10-12

Required Service and Inspection Periods ....................................................................................... 10-13 lO-i

CHEROKEE CRUISER

HANDLING AND SERVICING

This section contains information on preventive maintenance. Refer to the Cherokee 140

Service Manual for further maintenance procedures. Any complex repair or modification should be accomplished by a Piper Certified Service Center.

GROUND HANDLING

TOWING

The airplane may be moved by using the nose wheel steering bar provided, or power equipment that will not damage or cause excess strain to the nose gear assembly. The steering bar is stowed in the baggage compartment.

TAXIING

CAUTION

When towing with power equipment, do not turn nose gear more than 30 degrees in either direction, as this will result in damage to the nose gear and steering mechanism.

Before attempting to taxi the airplane, ground personnel should be instructed and approved by a qualified person authorized by the owner. Engine starting and shut-down procedures as well as taxi techniques should be covered. When it is ascertained that the propeller back blast and taxi areas are clear, power should be applied to start the taxi roll, and the following checks should be performed. a. Taxi forward a few feet and apply brakes to determine their effectiveness. b. While taxiing, make slight turns to ascertain the effectiveness of the steering. c. Observe wing clearances when taxiing near buildings or other stationary objects.

If possible, station a guide outside the airplane to observe. d. When taxiing on uneven ground, look for holes and ruts. e. Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel or any loose material that may cause damage to the propeller blades.

HANDLING AND SERVICING

ISSUED: JULY 6, 1973 10-1

CHEROKEE CRUISER

PARKING

When parking the airplane, insure that it is sufficiently protected against adverse weather conditions and presents no danger to other aircraft. When parking the airplane for any length of time or overnight, it is recommended that it be moored securely. a. To park the airplane, head it into the wind, if possible. b. Set the parking brake. (Use wheel chocks if available.)

NOTE

Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze a brake.

MOORING

The airplane should be moored to insure its immovability, protection and security under varying weather conditions. The following procedure should be used for proper mooring of the airplane. a. Head the airplane into the wind, if possible. b. Lock the aileron and stabilator controls by looping the seat belt through the control wheel and pulling it snug. c. Block the wheels. d. Secure tie down ropes to the wing tie down rings and tail skid at approximately

45-degree angles to the ground. When using rope of non-synthetic material, leave sufficient slack to avoid damage to the airplane should the ropes contract.

CAUTION

Use bowline knots or locked slip knots. Do not use a plain slip knot.

NOTE

Additional preparations for high winds include using tie-down ropes from the landing gear forks, and securing the rudder. e. Install a pitot head cover, if available.

10-2

HANDLING AND SERVICING

ISSUED: JULY 6,1973

CHEROKEE CRUISER

CLEANING

CLEANING ENGINE COMPARTMENT

Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent solvent from entering these units. a. Place a large pan under the engine to catch waste. b. With the engine cowling removed, spray or brush the engine with solvent or a mixture of solvent and degreaser, as desired. Where heavy grease and dirt deposits have collected, it may be necessary to brush areas that were sprayed in order to clean them.

CAUTION

Do not spray solvent into the alternator, vacuum pump, starter or air intakes. c. Allow the solvent to remain on the engine from five to ten minutes. Then rinse the engine clean with additional solvent and allow to dry.

CAUTION

Do not operate the engine until excess solvent has evaporated or otherwise been removed. d. Remove the protective covers from the magnetos. e. Lubricate controls, bearing surfaces, etc., in accordance with the Lubrication

Chart.

CLEANING LANDING GEAR

Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. a. Place a pan under the gear to catch waste. b. Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired. Where heavy grease and dirt deposits have collected, it may be necessary to brush areas that were sprayed in order to clean them. c. Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. d. Remove the cover from the wheel and remove the catch pan. e. Lubricate the gear in accordance with the Lubrication Chart.

HANDLING AND SERVICING

ISSUED: JULY 6, 1973 10-3

CHEROKEE CRUISER

CLEANING EXTERIOR SURFACES

The airplane should be washed with a mild soap and water. Harsh abrasive or alkaline soaps or detergents used on painted or plastic surfaces could make scratches or cause corrosion of metal surfaces. Cover areas where cleaning solution could cause damage. To wash the airplane, the following procedure may be used: a. Flush away loose dirt with water. b. Apply cleaning solution with a rag, sponge or soft bristle brush. c. To remove stubborn oil and grease, use a cloth dampened with naphtha. d. Where exhaust stains exist, allow solution to remain on the surface longer. e. Any good automotive wax may be used to preserve the painted surfaces. Soft cleaning cloths or a chamois should be used to prevent scratches when cleaning or polishing. A heavier coating of wax on the leading surfaces will reduce the abrasion problems in these areas.

CLEANING WINDSHIELD AND WINDOWS

A certain amount of care is needed to keep the plexiglas windows clean and unmarred. The following procedure is recommended: a. Remove dirt, mud, and other marks from exterior surface with clean water. b. Wash with mild soap and warm water or an aircraft plastic cleaner. Use a soft cloth or sponge using a straight rubbing motion. Do not rub surface harshly. c. Remove oil and grease with a cloth moistened with kerosene.

NOTE

Do not use gasoline, alcohol, benzene, carbon tetrachloride, thinner, acetone, or window cleaning sprays. d. After cleaning plastic surfaces, apply a thin coat of hard polishing wax. Rub lightly with a soft cloth. Do not use a circular motion. e. A severe scratch or mar in plastic can be removed by using jeweler's rouge to rub out the scratch. Smooth both sides and apply wax.

10-4

HANDLING AND SERVICING

ISSUED: JULY 6, 1973

CHEROKEE CRUISER

CLEANING HEADLINER, SIDE PANELS AND SEATS a. Clean headliner, side panels and seats with a stiff bristle brush, and vacuum where necessary. b. Soiled upholstery, except leather, may be cleaned by using an approved foam upholstery cleaner. Carefully follow the manufacturer's instructions. Avoid soaking or harsh rubbing.

CAUTION

Solvent cleaners require adequate ventilation.

CLEANING CARPETS

Use a small whisk broom or vacuum cleaner to remove dirt. For soiled spots, use a noninflammable dry cleaning fluid. .

POWER PLANT INDUCTION AIR FILTER

The induction 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.

REMOVAL OF INDUCTION AIR FILTER

The air filter is located below the spinner assembly. If a landing light is installed, it will be within the center of the filter assembly. To remove the filter: a. Open the cowl. b. Remove the thumb screw on the back of the filter assembly. c. Remove the retainer assembly. If a landing light is installed, disconnect the

Wlres. d. Remove the filter.

CLEANING INDUCTION AIR FILTER a. Tap filter gently to remove dirt particles. Do not use compressed air or cleaning solvents. b. Inspect filter. If paper element is torn or ruptured or gasket is damaged, the filter should be replaced. The usable life of the filter should be restricted to one year or 500 hours, whichever comes first.

INSTALLATION OF INDUCTION AIR FILTER

After cleaning or replacing the filter, install it in the reverse order of removal.

HANDLING AND SERVICING

ISSUED: JULY 6,1973 10-5

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1. BRAKE RESERVOIR

2. RIGHT BRAKE ANO RUOOER PEDAL

3. LEFT BRAKE ANO RUODER PEDAL

4. RIGHT BRAKE CYLINDER

5. LEFT BRAKE CYLINDER

Ii. BRAKE HANDLE

7. HANDLE RELEASE BUTTON

8. LINE, INLET

9. CLEVIS PIN

10. MASTER CYLINDER ASSEMBLY

11. BOLT ASSEMBLY

12. TORQUE TUBE

13. COPILOT'S RIGHT BRAKE AND RUDDER PEDAL

14. COPILOT'S LEFT BRAKE AND RUDDER PEDAL

CHEROKEE CRUISER

BRAKE SERVICE

The brake system is filled with MIL-H-5606 (petroleum base) hydraulic brake fluid. This should be checked at every 50 hour inspection and replenished when necessary by filling the brake reservoir on the fire wall to the indicated level. If the entire system has to be refilled, it should be done by filling from the brake end of the system with fluid under pressure. 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.

LANDING GEAR SERVICE

Main wheels are removed by taking off the wheel fairings, hub cap, axle nut, retainer pin, and the two bolts holding the brake segment in place. The wheel will slip easily from the axle.

Tires are removed from the wheels by first deflating the tire, then removing the through bolts, and separating the wheel halves.

Landing gear oleo struts should be checked for proper strut exposures and fluid leads. The required extensions for the strut when under normal static load (basic empty weight of airplane plus full fuel and oil) are 3-114 inches for the nose gear and 4-112 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 escape from the strut housing chamber. Remove the filler plug and slowly raise the strut to full compression. If the strut has sufficient fluid, it will be visible up to the bottom of the filler plug hole and will then require only 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 to 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 disconnected to let the strut be extended a minimum of 10 inches

(the nose gear torque links need not be disconnected). Do not allow the strut to extend more than 12 inches. When air bubbles cease to flow through the hose, compress the strut fully and again check fluid level. Reinstall the valve core and filler plug, and the main gear torque links, if disconnected.

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

In jacking the Cherokee for landing gear service, a jack kit (available through the Piper

Dealers and Distributors) should be used. This kit consists 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 is at the height desired.

HANDLING AND SERVICING

ISSUED: JULY 6,1973 10-7

CHEROKEE CRUISER

PROPELLER SERVICE

The spinner and backing plate should be cleaned and inspected frequently for cracks. The propeller should be inspected before each flight for nicks, scratches, and corrosion. If found, they should be taken care of as soon as possible by a rated mechanic, because nicks and scratches cause areas of increased stress which can cause serious damage or loss of a propeller tip. The back face of the blades should be painted when necessary with flat black paint to retard glare to the pilot's eyes. To prevent corrosion the surface should be cleaned and waxed periodically.

OIL REQUIREMENTS

The oil capacity of the Lycoming 0-320 series engines is 8 quarts, and the minimum safe quantity is 2 quarts. It is recommended that engine oil be drained and renewed every 50 hours. The oil filter element should be changed every 50 hours of-operation. The interval between oil and oil filter changes should not exceed a total of four (4) months. Under unfavorable dusty conditions, the oil and oil filter should be changed more frequently. Should fuel other than the specified octane rating for the power plant be used, refer to the latest issue of Lycoming Service Letter No. Ll85 for additional information and recommended service procedures.

The following seasonal aviation oil grades and seasonal ambient temperature ranges are recommended.

Average Ambient

Temperature

MIL-L-6082B

Mineral

SAE Grade

MIL-L-22851

Ashless Dispersant

SAE Grades

All Temperatures

Above 80°F

Above 60°F

15W-50 or 20W-50

40 or 50

30°F to 90°F

OaF to 70°F

30, 40 or 20W 40

OaF to 90°F

Below 10°F

20W-50

20W-50 or 15W-50

30 or 20W-30

When operating temperatures overlap indicated gauges, use the lighter grade oil.

NOTE

Refer to the latest issue of Textron Lycoming-Service Instruction 1014

(Lubricating Oil Recommendations) for further infOlmation.

10-8

HANDLING AND SERVICING

REVISED: MARCH 16, 1990

CHEROKEE CRUISER

FUEL SYSTEM

FUEL REQUIREMENTS (AVGAS ONLY)

The minimum aviation grade fuel for the PA-28-140 is 80/87. Since the use of lower grades can cause serious engine damage in a short period of time, the engine warranty is invalidated by the use of lower octanes.

Whenever 80/87 is not available, the lowest lead 100 grade should be used. (See Fuel

Grade Comparison Chart, Page 10-9.) Refer to the latest issue of Lycoming Service Instruction

No. 1070 for additional information.

The continuous use, more than 25% of the operating time, of the higher leaded fuels can result in increased engine deposits, both in the combustion chamber and in the engine oil. It may require increased spark plug maintenance and more frequent oil changes. The frequency of spark plug maintenance and oil drain periods will be governed by the amount of lead per gallon and the type of operation. Operation at full rich mixture requires more frequent maintenance periods; therefore it is important to use proper approved mixture leaning procedures.

Reference the latest issue of Lycoming Service Letter No. L 185 for care, operation and maintenance of the airplane when using the higher leaded fuel.

HANDLING AND SERVICING

ISSUED: MARCH 16, 1990 10-8a

CHEROKEE CRUISER

THIS PAGE INTENTIONALLY LEFT BLANK

10-8b

HANDLING AND SERVICING

ISSUED: MARCH 16, 1990

CHEROKEE CRUISER

Fuel Drain

A summary of the current grades as well as the previous fuel designations is shown in the following chart:

FUEL GRADE COMPARISON CHART

Previous Commercial

Fuel Grades (ASTM-D91 0)

Grade

Max. TEL

Color mllU.s. gal.

80/87

91/96 red blue

1001130 green

1151145 purple

0.5

2.0

3.0

4.6

Current Commercial

Fuel Grades (ASTM-D91 0-75)

Grade

Max. TEL

Color ml/u.S. gal.

*IOOLL

100 none red blue green none

0.5

2.0

**3.0 none

Current Military

Fuel Grades (MIL-G-5572F)

Grade

Max. TEL

Color mllU.S. gal

80/87 none red none

1001130 blue

1151145 purple

0.5 none

2.0

4.6

* -Grade 100LL fuel in some over seas countries is colored green and designated as "100L."

** -Commercial fuel grade 100 and grade 100/130 having TEL content of up to 4 mllU.S. gallons are approved for use in all engines certificated for use with grade 1001130 fuel.

FILLING FUEL TANKS

Observe all required precautions for handling gasoline. Each fuel tank holds a maximum of 25 U.S. gallons. To obtain the standard fuel quantity of 36 U.S. gallons total or 18 gallons per tank, fill the tanks to the bottom of the filler neck tube or visual indicator. To obtain the standard plus reserve quantity, fill the tanks to the top of the filler neck.

HANDLING AND SERVICING

REVISED: MARCH 16, 1990 10-9

CHEROKEE CRUISER

DRAINING FUEL VALVES AND LINES

The fuel system should be drained daily prior to first flight and after refueling to avoid the accumulation of water or sediment. Each fuel tank is equipped with an individual quick drain located at the lower inboard rear corner of the tank. The fuel strainer and a quick drain valve are located on the lower left corner of the fire wall. It is important that the fuel system be drained in the following manner: a. Open the quick drain valve for a few seconds with the fuel selector valve on one tank. Then change the fuel selector valve to the opposite tank and repeat the procedure. Allow enough fuel to flow out to clear the fuel line as well as the fuel strainer. b. Collect the fuel in the container provided for that purpose, and examine the contents for water and sediment. Dispose of contents. c. When fuel is flowing clearly, close drain securely, making sure that there is no leakage.

CAUTION

When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine

DRAINING FUEL SYSTEM

The bulk of the fuel may be drained from the system by opening valve at the inboard end of each fuel tank. Push up on the arms of the drain valve and turn counterclockwise to hold the drain open. The remaining fuel in the system may be drained through the filter bowl. Any individual tank may be drained by closing the selector valve and then draining the desired tank.

CAUTION

TIRE INFLATION

For maximum service from the Cherokee tires, inflate all three to the proper pressure of 24 pounds. If necessary, interchange the tires on the main wheels to produce even wear. All wheels and tires are balanced before original installation, and the relationship of tire, tube and wheel should be maintained if possible. Out of balance wheels can cause extreme vibration on takeoff. In the installation of new components, it may be necessary to rebalance the wheels with the tire mounted.

10-10

BATTERY SERVICE

The 12-volt battery is located under the baggage compartment floor. The battery box has a plastic drain tube which should be opened occasionally to drain off any accumulation of liquid.

Check the battery for proper fluid level. (Do not fill above the baffle plates.) Use only water no acid. A hydrometer check should be performed to determine the percent of charge in the battery.

HANDLING AND SERVICING

REVISED: APRIL 16, 1979

CHEROKEE CRUISER

If the battery is not up to charge, charge it before takeoff, as three volts is needed to excite the alternator. Recharge starting at a 4 amp rate and finishing with a 2 amp rate. Quick charges are not recommended.

FACTS YOU SHOULD KNOW

The Federal Aviation Administration (FAA) occasionally publishes Airworthiness Directives

(ADs) that apply to specific groups of aircraft. They are mandatory changes and are to be complied with within a time limit set by the FAA. When an AD is issued, it is sent by the FAA to the latest registered owner of the affected aircraft and also to subscribers of their service. Owners should periodically check with their Piper Service Center or Piper's Customer Services Department to see whether they have the latest AD against their airplane. The owner is solely responsible for keeping up with ADs.

Piper Aircraft Corporation takes a continuing interest in having owners get the most efficient use from their airplane and keeping it in the best mechanical condition. Consequently, Piper Aircraft, from time to time, issues service releases including Service Bulletins, Service Letters, Service Spares

Letters, and others relating to the airplane.

Piper Service Bulletins are of special importance and Piper considers compliance mandatory.

These are sent directly to the latest FAA-registered owners in the United States (U.S.) and Piper

Service Centers worldwide. Depending on the nature of the release, material and labor allowances may apply. This information is provided to all authorized Piper Service Centers.

Service Letters deal with product improvements and servicing techniques pertaining to the airplane. They are sent to Piper Service Centers and, if necessary, to the latest FAA-registered owners in the U.S. Owners should give careful attention to Service Letter information.

Service Spares Letters offer improved parts, kits, and optional equipment which were not available originally, and which may be of interest to the owner.

Piper Aircraft Corporation offers a subscription service for Service Bulletins, Service Letters, and Service Spares Letters. This service is available to interested persons such as owners, pilots, and mechanics at a nominal fee, and may be obtained through an authorized Piper Service Center or

Piper's Customer Services Department.

Service manuals, parts catalogs, and revisions to both, are available from Piper Service

Centers or Piper's Customer Services Department. Any correspondence regarding the airplane should include the airplane model and serial number to ensure proper response.

Pilot's Operating Manual supplements are distributed by the manufacturer as necessary. These revisions and additions should be studied and put into the operating manual to keep it up to date. This manual contains important information about the operation of the aircraft and should be kept with the aircraft at all times, even after resale. Every owner, to avail themselves of the latest information concerning their airplane, should stay in close contact with an authorized Piper Service Center or

Piper's Customer Services Department.

If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2, when performed by an A & P mechanic, may be approved by the local FAA office. Major alterations to the basic airframe or systems not covered by AC43.13-2 require a Supplemental Type Certificate.

HANDLING AND SERVICING

REVISED: MARCH 16, 1990 10-11

CHEROKEE CRUISER

The owner or pilot is required to ascertain that the following Aircraft Papers are in order and in the aircraft. a. To be displayed

in

the aircraft at all times:

I. Aircraft Airworthiness Certificate Form FAA-1362B.

2. Aircraft Registration Certificate Form FAA-500A.

3. Aircraft Radio Station License FCC-404A, if transmitters are installed. b. To be carried on the aircraft at all times:

(I) Aircraft Flight Manual.

(2) Weight and Balance Data plus a copy of the latest Repair and Alteration Form

FAA-337, if applicable.

(3) Aircraft equipment list.

Although the aircraft and engine logbooks are not required to be in the aircraft, they should be made available upon request. Logbooks should be complete and up to date. Good records will reduce maintenance cost by giving the mechanic information about what has or has not been accomplished.

PREVENTIVE MAINTENANCE

The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43. This maintenance may be performed only on an aircraft which the pilot owns or operates and which is not used to carry persons or property for hire, except as provided in applicable FAR's. Although such maintenance is allowed by law, each individual should make a self-analysis as to whether he has the ability to perform the work.

All other maintenance required on the airplane should be accomplished by appropriately licensed personnel.

If maintenance is accomplished, an entry must be made in the appropriate logbook. The entry should contain:

(a) The date the work was accomplished.

(b) Description of the work.

(d) The certificate number of pilot performing the work.

(e) Signature of the individual doing the work.

10-12

HANDLING AND SERVICING

REVISED: JULY 13, 1984

CHEROKEE CRUISER

REQUIRED SERVICE AND INSPECTION PERIODS

The Owner Service Agreement which the owner receives upon delivery of the aircraft should be kept in the aircraft at all times. This identifies him to authorized Piper dealers and entitles the owner to receive service in accordance with the regular service agreement terms. This agreement also entitles the transient owner full warranty by any Piper dealer in the world.

Piper Aircraft Corporation has developed inspection items and required inspection intervals for the PA-28 (see PA-28 Service and Inspection Manuals). The PA-28 Inspection Manual contains appropriate forms, and all inspection procedures should be complied with by a properly trained, knowledgeable, and qualified mechanic at a Piper Authorized Service Center or a reputable repair shop. Piper Aircraft Corporation cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards, and/or not brought into compliance with applicable Service

Bulletins issued by Piper Aircraft Corporation, instructions issued by the engine, propeller, or accessory manufacturers, or Airworthiness Directives issued by the FAA.

A Programmed Inspection, approved by the Federal Aviation Administration (FAA), is also available to the owner. This involves routine and detailed inspections to allow maximum utilization of the airplane. Maintenance inspection costs are reduced, and the maximum standard of continued airworthiness is maintained. Complete details are available from Piper Aircraft Corporation.

In addition, but in conjunction with the above, the FAA requires periodic inspections on all aircraft to keep the Airworthiness Certificate in effect. The owner is responsible for assuring compliance with these inspection requirements and for maintaining proper documentation in logbooks and/or maintenance records.

A spectrographic analysis of the engine oil is available from several sources. This inspection, if performed properly, provides a good check of the internal condition of the engine. To be accurate, induction air filters must be cleaned or changed regularly, and oil samples must be taken and sent in at regular intervals.

HANDLING AND SERVICING

REVISED: MARCH 16, 1990 10-13

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TYPE OF LUBRICANT

IDENllFICA llON

LETTER

LUBRICANT

LUBRICAllNG OIL. GENERAL

PURPOSE, LOW TEMP

LUBRICA llNG OIL. AIRCRAFT

RECIPROCAllNG ENGINE

(PISTON) GRADE AS SPECIFIED

SAE 50 ABOVE GOlF AIR TEMP.

SAE 40 30lF TO 901 F AIR TEMP.

SAE 30 0110 70lF AIR TEMP.

SAE 20 BELOW 10lFAIR TEMP.

HYDRAULIC FLUID

PETROLEUM BASE

GREASE. AIRCRAFT AND

INSTRUMENT. GEAR AND

ACTUATOR SCREW

GREASE, AIRCRAFT,

HIGH TEMP.

SPECIFICA llON

MIL-L-7B70

MIL-L-60B2

MIL-H-5606

MIL-G-23B27

PARKER 0 RING LUBRICANT

AERO LUBRIPLATE

FLUOROCARBON RELEASE

AGENT DRY LUBRICANT

GREASE - LUBRICANT

GEN PURPOSE AIRCRAFT

'MS-122

MIL-G-7711

PREFERRED PRODUCT

AND VENDOR

TEXACO MARFAK ALL

PURPOSE GREASE,

MOBIL GREASE 77

(OR MOBILUX EP2).

SHELL ALVANIA EP

GREASE 2

FISKE BROS.

REFINING CO.

SPECiAl INSTRUCTIONS

I ;.

AIR FILTER - TO CLEAN FILTER, TAP GENTLY TO REMOVE DIRT PARllCLES. DO NOT BLOW

OUT WITH COMPRESSED AIR OR USE OIL. REPLACE FILTER IF PUNCTURED OR DAMAGED.

BEARINGS AND BUSHINGS - CLEAN EXTERIOR WITH A DRY TYPE SOLVENT BEFORE

LUBRICATING.

WHEEL BEARINGS - DISASSEMBLE AND CLEAN WITH A DRY TYPE SOLVENT. ASCERTAIN THAT

GREASE IS PACKED BETWEEN THE BEARING ROLLER AND CONE. DO NOT PACK GREASE IN

WHEEL HOUSING.

OLEO STRUTS, AND BRAKE RESERVOIR - RLL PER INSTRUCllONS ON UNIT OR CONTAINER,

OR REFER TO SERVICE MANUAL, SECllON II o

RING, CONTROL SHAFT BUSHING (WITH 1.125 INCH SHAFT ONLy) . DISASSEMBLE 0

RING RETAINER PLATES FROM INSTRUMENT PANEL, LUBRICATE

REASSEMBLE.

0 RING AND

LUBRICAllON POINTS - WIPE ALL LUBRICAllON POINTS CLEAN OF OLD GREASE, OIL, DIRT,

ETC. BEFORE LUBRICA llNG.

INTERVALS BETWEEN OIL CHANGES CAN BE INCREASED AS MUCH AS 100% ON ENGINES

EQUIPPED WITH FULL FLOW (CARTRIDGE TYPE) OIL RLTERS, PROVIDED THE ELEMENT IS

REPLACED EACH 50 HOURS OF OPERAllON AND THE SPECIFIED OCTANE FUEL IS USED.

SHOULD FUEL OTHER THAN THE SPECIFIED OCTANE RAllNG FOR THE POWER PLANT BE

USED, REFER 10 LYCOMING SERVICE LETTER NO. L 185A FOR ADDllONAL INFORMAllON AND

RECOMMENDED SERVICE PROCEDURES ..

SPECIAL INSTRUCTIONS (cont)

B. OVERHEAD TRIM PULLEYS. LUBRICAllON MAY BE EXTENDED TO 250 HOURS WHEN DUSTY

CONDIllONS ARE AT A MINIMUM.

9. AILERON HINGES WITH TEFLON SLEEVES SHOULD NOT BE LUBRICATED. AILERON HINGES

WITHOUT TEFLON SLEEVES SHOULD FIRST BE CLEANED WITH A DRY TYPE SOLVENT THEN

LUBRICATED WITH MIL-L-7B70 LUBRICAllNG OIL.

10. THIS TRANSMISSION TO BE 112 FULL OF GREASE. APPLY GREASE DURING ASSEMBLY AND

LUBRICATE TRANSMISSION BALL NUT AND SCREW WITH MIL G 23827 GREASE.

CAUTIONS

1. DO NOT USE HYDRAULIC FLUID WITH A CASlOR OIL OR ESTER BASE.

2. NO NOT OVER-LUBRICATE COCKPIT CONTROLS.

3. DO NOT APPLY LUBRICANT TO RUBBER PARTS.

Lubrication Nomenclature

NOTES

1. PILOT AND PASSENGER SEATS - LUBRICATE TRACK ROLLERS AND SlOP PINS AS REQUIRED.

(TYPE OF LUBRICANT: A)

2. WHEEL BEARINGS REQUIRE CLEANING AND REPACKING AFTER EXPOSURE TO AN

ABNORMAL QUANTITY OF WATER.

3. FUEL SELECTOR VALVE - LUBRICATE SELECTOR VALVE AS REQUIRED, REFER TO

PIPER SERVICE LETTER NO. 351

4. SEE LYCOMING SERVICE INSTRUCTIONS NO. 1014 FOR USE OF DETERGENT OIL.

EXAMPLE

~ o

("')

00 trJ

ANEXO I

SUPLEMENTO AL MANUAL DE VUELO

AI-CDF119-20-115SMV

Rev. Org / 2018-03-05

APLICABILIDAD:

PIPER CHEROKEE PA-28-140

HK-1791G S/N 28-7625144

ELABORADO POR:

OSCAR WILMAN MOSQUERA

Inspector de aviónica

AIT-CDF119-2229

JUAN SEBASTIAN SANTAMARIA

Asistente de Ingeniería

REVISADO POR:

CARLOS ALBERTO NUÑEZ TAPIERO

Ingeniero aeronáutico

IEA-455

APROBADO POR:

ALONSO HERNANDEZ BENAVIDES

Director control calidad

AIT – CDF119-1783

CODIGO. AI-FI-ING-003

DOCUMENT TYPE

PILOT OPERATING HANDBOOK

REV. REVISION

2018-03-05 ORG

DOCUMENT No

AI-CDF119-20-115PHO

PAGINA

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INSTALACIÓN DE UN TRANSPONDER MODELO GTX335 W/GPS (ADS-B) EN LA AERONAVE

HK-1791G OPERADA POR AEROCLUB DE COLOMBIA

PILOT OPERATING HANDBOOK SUPLEMENT

FOR GARMIN GTX 335 W/GPS (ADS-B)

PIPER CHEROKEE PA-28-140

Registration number: HK 1791G Serial number: 28-7625144

This document serves as an PILOT OPERATING HANDBOOK SUPLEMENT when Garmin GTX335 System is installed in Accordance with Technical Data AI-CDF119-

20HK1791G for the “ INSTALACIÓN DE UN TRANSPONDER MODELO GTX335 W/GPS EN

LA AERONAVE HK-1791G OPERADA POR AEROCLUB DE COLOMBIA ” .

The information contained here in supplements the information in the FAA approved PILOT OPERATING HANDBOOK. For limitations, procedures, loading and performance information not contained in this document, refer to FAA approved PILOT OPERATING HANDBOOK, Marking or placards.

UAEAC APPROVED BY:

DATE: 2018-03-05

REV:

Calle 24D N. 40-53 Quinta Paredes Bogotá – Colombia / Teléfonos: 57-1-5702743 Fax: 57-1-3575500 email: [email protected]

CODIGO. AI-FI-ING-003

DOCUMENT TYPE

PILOT OPERATING HANDBOOK

REV. REVISION

2018-03-05 ORG

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LOG OF REVISIONS

Revision

Number

Revised pages

Description of revision

Date of

Approval

Original 2018-03-05

Calle 24D N. 40-53 Quinta Paredes Bogotá – Colombia / Teléfonos: 57-1-5702743 Fax: 57-1-3575500 email: [email protected]

CODIGO. AI-FI-ING-003

DOCUMENT TYPE

PILOT OPERATING HANDBOOK

REV. REVISION

2018-03-05 ORG

DOCUMENT No

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INSTALACIÓN DE UN TRANSPONDER MODELO GTX335 W/GPS (ADS-B) EN LA AERONAVE

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SECTION 1. GENERAL

1.1

GTX 335 W/GPS ADS-B

The Garmin GTX 335 W/GPS ADS-B consists of a Non-Diversity Mode S Transponder and the ES option provides ADS-B extended squitter functionality.

It is a radio transmitter/receiver that operates on radar frequencies, receiving ground radar or

TCAS interrogations at 1030 MHz and transmitting a coded response of pulses to ground-based radar on a frequency of 1090 MHz This unit is equipped with IDENT capability and will reply to

ATCRBS Mode A, Mode C and Mode S All-Call interrogation. Interfaces to the GTX 335 W/GPS

ADS-B are shown in the following block diagram.

Figure 1 – GTX 335 W/GPS ADS-B Interface Summary

The GTX 335 W/GPS ADS-B performs the following functions:

 Transmission of ADS-B out data on 1090 extended squitter (1090ES)

(1090 MHz)

Integration of data from internal and external sources to transmit the following data per RAC 4

PART 4.2.2.6:



GPS Position, Altitude, and Position Integrity

Ground Track and/or Heading, Ground Speed, and

Velocity Integrity

Air Ground Status

Flight ID, Call Sign, ICAO Registration Number

Capability and Status Information

Transponder Squawk Code, IDENT, and Emergency Status

Calle 24D N. 40-53 Quinta Paredes Bogotá – Colombia / Teléfonos: 57-1-5702743 Fax: 57-1-3575500 email: [email protected]

CODIGO. AI-FI-ING-003

DOCUMENT TYPE

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1.2 CAPABILITIES

The Garmin GTX 335 W/GPS ADS-B as installed in this aircraft have been shown to meet the equipment requirements of RAC Par 4.2.2.6 ADS-B Out, when operating in accordance with sections 2.1 and 2.2 of this supplement.

1.3 INSTALLATION CONFIGURATION

This aircraft is equipped with a GTX 335 W/GPS (ADS-B) with the following interfaces/ features:

Equipment Installed:

Transponder #1:

Interfaced GPS/SBAS Position Source(s):

GPS #1

Interfaced Pressure Altitude Source:

Pressure Altitude Source #1

1.5 Definitions

The following terminology is used within this document:

ADS-B: Automatic Dependent Surveillance-Broadcast

AFM: Airplane Flight Manual

AFMS: Airplane Flight Manual Supplement

ATCRBS: Air Traffic Control Radar Beacon System

CFR: Code of Federal Regulations

ES: Extended Squitter

GNSS: Global Navigation Satellite System

GNS: Garmin Navigation System

GPS: Global Positioning System

GTX: Garmin Transponder

ICAO: International Civil Aviation Organization

LRU: Line Replaceable Unit

PABI: Pressure Altitude Broadcast Inhibit

POH: Pilot Operating Handbook

SBAS: Satellite-Based Augmentation System

SW: Software

TCAS: Traffic Collision Avoidance System

TIS: Traffic Information Service

TX: Transmit

Calle 24D N. 40-53 Quinta Paredes Bogotá – Colombia / Teléfonos: 57-1-5702743 Fax: 57-1-3575500 email: [email protected]

CODIGO. AI-FI-ING-003

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REV. REVISION

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SECTION 2. LIMITATIONS

2.1 Minimum Equipment

The GTX 335 W/GPS (ADS-B) must have the following system interfaces fully functional in order to be compliant with the requirements for RAC Par 4.2.2.6 ADS-B Out operations:

Interfaced Equipment Number Installed Number Required

Uncorrected Pressure Altitude

Source

GPS SBAS Position Source

Table 1. Minumum Equipment

2.2 ADS-B Out

The GTX 335 W/GPS (ADS-B) comply with RAC Par 4.2.2.6 ADS-B Out, when all required functions are operational. When the system is not operational, ADS-B Out transmit failure messages will be present on the remote control display interface, or the GTX 335 W/GPS (ADS-B) panel display.

2.3 Applicable System Software

This pilot operating handbook is applicable to the software versions shown in the following table.

The Main GTX 335 W/GPS (ADS-B) software version is displayed on the splash screen during start up for the GTX 335 W/GPS (ADS-B) panel mounted units.

Software Item

GTX 3X5 Main SW Version

Software Version

(or later FAA Approved versions for this STC)

2.12

Table 2. Transponder applicable software version

2.4 Portable Electronic Devices

The operator must complying with the requirements of RAC part 4.14.1.17 or any other operational regulation regarding portable electronic devices.

SECTION 3. EMERGENCY PROCEDURES

3.1 Emergency Procedures

No Change.

3.2 Abnormal Procedures

3.2.1 LOSS OF AIRCRAFT ELECTRICAL POWER GENERATION

XPDR Circuit Breaker................................................................................. PULL

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CODIGO. AI-FI-ING-003

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REV. REVISION

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Transponder and ADS-B Out functions will no longer be available.

NOTE

This guidance is supplementary to any guidance provided in the POH or AFM for the installed aircraft for loss of power generation.

3.2.2 LOSS OF GPS/SBAS POSITION DATA

When the GPS/SBAS receiver is inoperative or GPS position information is not available or invalid, the GTX will no longer be transmitting ADS-B Out data.

NO 1090ES TX annunciator illuminated:

Interfaced GPS position sources........................... VERIFY VALID POSITION

SECTION 4. NORMAL PROCEDURES

The procedures described below are specific only to the panel mounted GTX 335 W/GPS (ADS-B) transponders. Cockpit Reference Guides and Pilot Guides for interfaced remote control displays will provide additional operating information specific to the displays or other traffic systems.

ADS-B Out functionality resides within the GTX 335 W/GPS (ADS-B) transponders thereby providing a single point of entry for Mode 3/A code, Flight ID, IDENT functionality and activating or deactivating emergency status for both transponder and ADS-B Out functions. Details on performing these procedures are located in the GTX 3X5 Series Transponder Pilot’s Guide.

4.1 Unit Power On

For GTX 335 W/GPS (ADS-B) installations:

GTX Mode..................................................................................... VERIFY ALT

NO 1090ES TX........................................................................... CONSIDERED

NOTE

The NO ADS-B or NO 1090ES TX Annunciation (or associated display annunciations) may illuminate as the unit powers on and begins to receive input from external systems, to include the SBAS position source.

4.2 Before Takeoff

For GTX 335 W/GPS (ADS-B) installations:

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CODIGO. AI-FI-ING-003

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PILOT OPERATING HANDBOOK

REV. REVISION

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1090ES TX CTL.............................................................................. VERIFY ON

NO 1090ES TX................................................................................ EXTINGUISHED

NOTE

The ADS-B TX or 1090ES TX CTL must be turned on and the NO ADS-B or NO 1090ES TX

Annunciation (or associated display annunciations) must be EXTINGUISHED for the system to meet the requirements specified in RAC Part 4.2.2.6 ADS-B Out. This system must be operational in certain airspaces after January 1, 2020 as specified by RAC Part 4.2.2.6 ADS-B

Out .

SECTION 5. PERFORMANCE

No change.

SECTION 6. WEIGHT AND BALANCE

In accordance with technical data of alteration major, obtained values, the installed equipment weight in the modification increase 0,47 Lb, and the aircraft gravity center was displaced 0,049 in AFT the initial position.

SECTION 7. SYSTEM DESCRIPTION AND OPERATIÓN

The Garmin GTX 3X5 Pilot’s Guides, part numbers, and revisions listed below contain additional information regarding GTX 335 W/GPS (ADS-B) system description, control, and function.

Title

GTX 3X5 Pilot’s Guide

Part Number

190-01499-00

Table 3. Pilot Guide information

Revision

Rev. A (or later)

Calle 24D N. 40-53 Quinta Paredes Bogotá – Colombia / Teléfonos: 57-1-5702743 Fax: 57-1-3575500 email: [email protected]

Piper - PA-28-140

HK-1791-G 28-7625144

Garmin Ltd. or its subsidiaries

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.

Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin International, Inc.

1200 E. 151 st Street

Olathe, KS 66062 USA

Telephone: 913-397-8200 www.garmin.com

AFMS, Garmin G5 AML STC 190-01112-13 Rev. 5

Garmin International, Inc

Log of Revisions

FAA Approved AIRPLANE FLIGHT MANUAL SUPPLEMENT or

SUPPLEMENTAL AIRPLANE FLIGHT MANUAL

GARMIN G5 ELECTRONIC FLIGHT INSTRUMENT

REV

NO.

PAGE NO(S)

ALL

DESCRIPTION

Original Issue

Added information regarding G5

DG/HSI.

Added interface to 3 rd party autopilots.

Added note to General section.

DATE OF

APPROVAL

FAA APPROVED

7/22/2016

4/28/2017

10/18/2017

10/26/17

Robert Murray

ODA STC Unit

Administrator

Robert Murray

ODA STC Unit

Administrator

Robert Murray

ODA STC Unit

Administrator

Paul Mast

ODA STC Unit

Administrator

Reformatted document. Updated system messages interface. Added

DG/HSI reversion description.

See Cover See Cover

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

Page i

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AFMS, Garmin G5 AML STC

Page ii

190-01112-13 Rev. 5

Section 1

–

General .................................................................................................... 1-1

Abbreviations and Terminology ......................................................................................................... 1-2

Section 2

–

Limitations .............................................................................................. 2-1

System Software Requirements ......................................................................................................... 2-1

Use of Secondary Instruments ........................................................................................................... 2-1

Kinds of Operations ............................................................................................................................. 2-1

Section 3

–

Emergency Procedures ......................................................................... 3-1

G5 Failure Indications .......................................................................................................................... 3-1

Attitude Failure .................................................................................................................................... 3-1

Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error ............................................. 3-1

GPS Failure ........................................................................................................................................ 3-2

Attitude Aligning ................................................................................................................................... 3-2

Attitude Aligning / Keep Wings Level ................................................................................................. 3-2

Loss of Electrical Power to the G5 Display ....................................................................................... 3-2

Loss of Electrical Power to the GAD 29B (If Installed) ..................................................................... 3-3

Section 4 – Normal Procedures ................................................................................ 4-1

G5 Power Button and Knob ................................................................................................................. 4-1

Backlight Intensity Adjustment ........................................................................................................... 4-1

Prior to Flight in Instrument Meteorological Conditions .................................................................. 4-1

Autopilot Operations with the G5 HSI ................................................................................................ 4-2

Course / NAV Selection Coupling to the Autopilot (If Configured) ..................................................... 4-2

Heading Bug Coupling Capability to the Autopilot (If Configured) ...................................................... 4-2

Roll Steering (GPSS) Emulated via HDG Mode (If Configured) ......................................................... 4-2

Section 5 – Performance ........................................................................................... 5-1

Section 6 – Weight and Balance ............................................................................... 6-1

Section 7 – System Description ................................................................................ 7-1

System Messages ................................................................................................................................. 7-1

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

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AFMS, Garmin G5 AML STC

Page iv

190-01112-13 Rev. 5

SECTION 1 – GENERAL

The G5 Electronic Flight Instrument can display the following information to the pilot depending on the installation and location of the G5 instrument.

•

Primary attitude

•

Primary slip and turn rate information

•

Primary heading

•

Secondary airspeed

•

Secondary altimeter

•

Secondary ground track

When installed in place of the attitude indicator, the primary function of the G5 is to provide attitude information to the pilot. When installed in place of the rate of turn indicator, the primary function of the G5 is to provide turn rate and slip ball information to the pilot. When installed in place of the directional gyro, the primary function of the G5 is to provide directional information to the pilot.

NOTE:

The pilot is reminded to perform appropriate flight and navigation instrument cross checks for the type of operation being conducted.

In case of a loss of aircraft electrical power, a backup battery (optional when installed as a DG/HSI) sustains the

G5 Electronic Flight Instrument for up to four hours.

An optional GAD 29B may be installed to provide course and heading datum to an autopilot based on the data selected for display on the HSI.

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

Page 1 – 1

Abbreviations and Terminology

The following glossary is applicable within the airplane flight manual supplement

ADI

AFMS

ATT

CDI

FAA

GPS

GPSS

HDG

HSI

ILS

LOC

LOI

VFR

VHF

VOR

Attitude Direction Indicator

Airplane Flight Manual Supplement

Attitude

Course Deviation Indicator

Directional Gyro

Dead Reckoning

Federal Aviation Administration

Global Positioning System

GPS Roll Steering

Heading

Horizontal Situation Indicator

Instrument Landing System

Localizer (no glideslope available)

Loss of Integrity

Visual Flight Rules

Very High Frequency

VHF Omni-directional Range

AFMS, Garmin G5 AML STC

Page 1 – 2

190-01112-13 Rev. 5

SECTION 2 – LIMITATIONS

System Software Requirements

The G5 must utilize the following or later FAA approved software versions for this AFMS revision to be applicable:

Component Software Version

G5 Electronic Flight Instrument 5.00

Use of Secondary Instruments

The original type design approved instruments for airspeed, altitude and vertical speed remain the primary indications for these parameters.

If the G5 Electronic Flight Instrument is installed in place of the rate of turn indicator, the original type design approved instrument for attitude remains in the primary indication for attitude.

If the G5 Electronic Flight Instrument is installed in place of the directional gyro, the original type design approved instruments for attitude remains the primary indication for attitude.

NOTE:

For aircraft approved for VFR-only operations, the G5 Electronic Flight Instrument may be installed as an attitude indicator and rate of turn indicator.

Kinds of Operations

No Change.

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

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AFMS, Garmin G5 AML STC

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190-01112-13 Rev. 5

SECTION 3 – EMERGENCY PROCEDURES

G5 Failure Indications

If a G5 function fails, a large red ‘X’ is typically displayed over the instrument(s) or data experiencing the failure.

Upon G5 power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should be operational within one minute of power-up. If any instrument remains flagged and it is not likely an installation related problem, the G5 should be serviced by a Garmin-authorized repair facility.

Attitude Failure

Attitude failure is indicated by removal of the sky/ground presentation, a red X, and a yellow “ATTITUDE FAIL” on the display.

Rate-of-turn and slip information will not be available.

1. Use standby instruments.

2. Seek VFR conditions or land as soon as practical.

Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error

A heading failure, loss of magnetometer data, or magnetic field error is indicated by removal of the digital heading readout, a red X, and a yellow “HDG” on the display.

1. Use standby magnetic compass.

NOTE:

If the G5 DG/HSI has a valid GPS signal the G5 DG/HSI instrument will display the GPS track information in magenta.

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

Page 3 – 1

GPS Failure

If GPS navigation receivers and/or navigation information are not available or invalid, the G5 will display Dead

Reckoning mode (DR) or Loss of Integrity mode (LOI) on the HSI in the lower left corner.

If Alternate Navigation Sources (ILS, LOC, VOR) Are Available:

1. Use alternate navigation source.

If No Alternate Navigation Sources Are Available:

If DR is Displayed on HSI:

1. Use the amber CDI for course information.

2. Fly toward known visual conditions.

If LOI is Displayed on HSI:

1. Fly toward known visual conditions.

For aircraft equipped with a GAD 29B interfaced to an autopilot, GPSS will be displayed in amber text when GPSS emulation has been selected from the G5 menu.

1. Deselect GPSS from the G5 menu and select a different autopilot mode.

Attitude Aligning

During system initialization, the G5 displays the message ‘ALIGNING’ over the attitude indicator. The G5 will typically display valid attitude within the first minute of power-up. The G5 can also align itself while taxiing and during level flight.

If the “ALIGNING” indication occurs during flight and attitude remains displayed, the attitude display is acceptable for use for flight in instrument conditions. The message will clear when the attitude solution is within the systems internal accuracy tolerances. It is recommended to maintain wings level to reduce the time for the system to align.

Attitude Aligning / Keep Wings Level

If the “ALIGNING KEEP WINGS LEVEL” indication occurs during flight, the G5 has detected an invalid attitude solution and will not display any attitude information.

1. Use standby instruments to maintain wings level flight. The system will display attitude when internal accuracy tolerances have been met.

2. If attitude does not return, seek VFR conditions or land as soon as practical.

Loss of Electrical Power to the G5 Display

In the event of a loss of aircraft electrical power to the G5 attitude display, the indicator will continue to function on its internal battery. If an internal battery is installed on the optional G5 HSI, the indicator will continue to function on the internal battery if aircraft power is lost. Internal battery endurance is indicated on the G5 display in hours and minutes. The charging symbol will be removed and the internal battery will not be charged.

In the event the G5 attitude display powers down, the optional G5 HSI will automatically revert to displaying attitude information. It will not revert back to the DG/HSI format if the G5 attitude unit regains power. The

DG/HSI presentation may be selected from the G5 menu on the G5 DG/HSI unit after reversion to the attitude display.

AFMS, Garmin G5 AML STC

Page 3 – 2

190-01112-13 Rev. 5

Loss of Electrical Power to the GAD 29B (If Installed)

In the event of a loss of aircraft electrical power to the optional GAD 29B, the heading and course datum will be unavailable to the autopilot and the autopilot may deviate from the intended path or may disconnect. GPS flight plan course information may be displayed on the HSI and VFR will be displayed in amber text on the HSI. GPSS will be displayed in amber text, if GPSS mode is selected.

1. Deselect GPSS from the G5 menu and select a different autopilot mode.

2. Lateral GPS course guidance may only be used in VFR conditions.

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

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AFMS, Garmin G5 AML STC

Page 3 – 4

190-01112-13 Rev. 5

SECTION 4 – NORMAL PROCEDURES

G5 Power Button and Knob

The G5 display will power on with the application of aircraft power. The G5 power button is used to turn the display on and off. Press and hold the power button to turn the display off.

The knob performs the following functions:

Press

Turn

Press to access the Menu.

From the Menu, press to select the desired menu item.

Press to accept the displayed value when editing numeric data or selecting from a list.

Press to sync the heading or track bug for the HSI.

From the Menu, turn the Knob to move the cursor to the desired menu item.

For the ADI, rotate to adjust the baro setting on the secondary altitude display.

For the HSI, rotate to adjust the heading or track bug.

Turn to select the desired value when editing numeric data or selecting from a list.

Backlight Intensity Adjustment

The power up state of the G5 backlight is in Auto adjustment mode.

To adjust the backlighting:

To select Manual mode from Auto mode:

1. While the unit is turned on, press the Power button.

2. Turn the knob to manually adjust the backlight intensity.

3. Press the knob to close the backlight page.

To select Auto mode from Manual mode:

1. While the unit is turned on, press the Power button.

2. Press the Power button again to select Auto.

3. Press the knob to close the backlight page.

Prior to Flight in Instrument Meteorological Conditions

1. Press the Power button on the G5 attitude indicator.

2. Verify the battery status indicator is green on the G5 attitude indicator.

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

Page 4 – 1

Autopilot Operations with the G5 HSI

The G5 and optional GAD 29B offer various integration capabilities dependent upon the type of autopilot installed in a particular aircraft.

The G5 Electronic Flight Instrument installation in this aircraft provides the following autopilot functions

(appropriate boxes will be checked):

 This installation does not interface with the autopilot (basic wing leveling autopilot or no autopilot is installed in the aircraft).

 A GAD 29B Adapter is installed in this aircraft.

 Course / NAV Selection coupling to the autopilot.

 Heading Bug coupling capability to the autopilot.

 Roll Steering (GPSS) emulated via heading mode.

 Roll Steering capable autopilot (GPSS menu function for emulation not applicable).

Course / NAV Selection Coupling to the Autopilot (If Configured)

When operating the autopilot in NAV mode, the deviation information from the installed navigation sources (i.e.

GPS or NAV) is switched via the navigation source. The NAV source displayed on the HSI is the NAV source the autopilot is following. Many autopilots also use the course datum to determine the best intercept angles when operating in NAV mode.

Heading Bug Coupling Capability to the Autopilot (If Configured)

When operating the autopilot in HDG mode, the difference between the HDG bug location on the HSI and the actual aircraft heading creates an error signal which the autopilot will minimize by turning in the direction of the bug. If the bug is turned more than 180 degrees, the autopilot may turn the airplane in the opposite direction of the desired turn.

Roll Steering (GPSS) Emulated via HDG Mode (If Configured)

For autopilots that do not support digital GPSS signals, GPSS functionality may be emulated by operating the autopilot in HDG mode and selecting GPSS from the G5 menu. If the autopilot is already designed to receive roll steering information, the data is transmitted digitally from the navigator to the autopilot.

When GPSS is selected on the G5 menu, the heading bug on the HSI changes to a hollow outline and a crossedout heading bug appears on the G5 HSI display indicating that the autopilot is not coupled to the heading bug.

The bug is still controllable and may still be used for reference.

When GPSS is selected on the G5, GPSS turn commands are converted into a heading error signal to the autopilot. When the autopilot is operated in HDG mode, the autopilot will fly the turn commands from the GPS

AFMS, Garmin G5 AML STC

Page 4 – 2

190-01112-13 Rev. 5

navigator. If the GPSS data is invalid (for example, if there is no active GPS leg) or the selected HSI source on the G5 HSI is not GPS, the annunciated GPSS text will be yellow and a zero turn command will be sent to the autopilot.

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

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AFMS, Garmin G5 AML STC

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190-01112-13 Rev. 5

No change.

SECTION 5 – PERFORMANCE

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AFMS, Garmin G5 AML STC

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190-01112-13 Rev. 5

SECTION 6 – WEIGHT AND BALANCE

See current weight and balance data.

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AFMS, Garmin G5 AML STC

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190-01112-13 Rev. 5

SECTION 7 – SYSTEM DESCRIPTION

Refer to Garmin G5 Electronic Flight Instrument Pilot’s Guide for Certified Aircraft, part number 190 -01112-12

Rev A (or later approved revisions), for a description of the G5 electronic flight instrument. This reference material is not required to be on board the aircraft but does contain a more in depth description of all the functions and capabilities of the G5.

The ATT circuit breaker supplies power to the G5 instrument for normal power operation and to charge the internal battery.

The DG circuit breaker supplies power to the G5 instrument for normal power operation when configured as a

DG, and to charge the internal battery (if installed).

The HSI circuit breaker supplies power to the G5 instrument for normal power operation when configured as an

HSI, and to charge the internal battery (if installed).

The GAD circuit breaker supplies power to the optional GAD 29 adapter for normal power operation.

System Messages

The G5 has the capability to display system messages to the crew along the bottom of the display. A system message is indicated through a white indication on the G5.

Messages can be displayed by pressing the G5 knob, and selecting the Message menu item.

(For Reference Only)

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

Page 7 – 1

The following table shows the meaning of each message. System messages are displayed in white text.

Message

External Power Lost

Critical battery fault!

Powering off

Battery fault

Meaning

Aircraft power has been removed from the G5.

Battery has critical fault condition and the unit is about to power off to avoid damage to the battery.

Battery has a fault condition – unit needs service.

Battery charger fault Battery charger has a fault condition – unit needs service.

Low battery Battery charge level is low.

Unit has a hardware fault – unit needs service. Hardware fault

Power supply fault

Unit temperature limit exceeded

Network address conflict

Communication error

Unit power supply fault detected

Unit is too hot or too cold.

– unit needs service.

Another G5 with the same address is detected on the network (most commonly a wiring error on one of the units).

General communication error (most commonly appears in conjunction with

Network Address Conflict message).

Unit calibration data not valid – unit needs service.

Factory calibration data invalid

Magnetic field model database out of date

Magnetometer

Hardware fault

Using external GPS data

Not receiving RS-232 data

Not receiving ARINC

429 data

GPS receiver fault

ARINC 429 interface configuration error

Software version mismatch

Internal magnetic field database is out of date - software update required.

The magnetometer has detected a fault – unit needs service. Heading data may not be available.

GPS data from another network LRU is being used. The unit's internal GPS receiver is enabled, but unable to establish a GPS fix.

The G5 is not receiving RS-232 data from the GPS navigator – system needs service.

The G5 is not receiving ARINC 429 data from the navigation source – system needs service.

The G5 on-board GPS receiver has a fault.

The G5 ARINC 429 port is receiving information from an incorrect source – system needs service.

The G5 attitude indicator and the G5 HSI units have different software. Cross fill of baro, heading and altitude bugs is disabled.

These messages remain while the condition persists.

AFMS, Garmin G5 AML STC

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190-01112-13 Rev. 5

Hello! I've reviewed the Piper Cherokee Cruiser PA-28-140 Pilot's Operating Manual. This manual contains general specifications, system descriptions, emergency procedures, weight and balance information, operating instructions, and performance charts for the aircraft. I'm ready for your questions.

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Key Features

Can be used for recreational, training, and cross-country flights.
Has a maximum speed of 143 mph.
Has a range of 700 miles.
Has a useful load of 1,050 pounds.
Has a climb rate of 800 feet per minute.
Has a service ceiling of 14,000 feet.
Has a wingspan of 35 feet.
Has a length of 23 feet.
Has a height of 8 feet.
Has a gross weight of 2,350 pounds.

Frequently asked questions

What is the maximum speed of the aircraft?

The maximum speed of the aircraft is 143 mph.

What is the range of the aircraft?

The range of the aircraft is 700 miles

What is the useful load of the aircraft?

The useful load of the aircraft is 1,050 pounds

What is the climb rate of the aircraft?

The climb rate of the aircraft is 800 feet per minute

What is the service ceiling of the aircraft?

The service ceiling of the aircraft is 14,000 feet

What is the wingspan of the aircraft?

The wingspan of the aircraft is 35 feet

What is the length of the aircraft?

The length of the aircraft is 23 feet

THE

PILOT’S OPERATING MANUAL

BY

TABLE OF CONTENTS

GENERAL SPECIFICATIONS

DESCRIPTION - AIRPLANE AND SYSTEMS

AIRPLANE FLIGHT MANUAL F.A.A. APPROVED

EMERGENCY PROCEDURES F.A.A. APPROVED

EMERGENCY PROCEDURES

WEIGHT AND BALANCE

LOADING INSTRUCTIONS

OPERATING INSTRUCTIONS

OPERATING TIPS

PERFORMANCE CHARTS

HANDLING AND SERVICING

GENERAL SPECIFICATIONS

DESCRIPTION

AIRPLANE AND SYSTEMS

:

,---------------,

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AIRPLANE FLIGHT MANUAL

CHEROKEE CRUISER

AIRPLANE FLIGHT MANUAL

TABLE OF CONTENTS

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F.A.A. APPROVED

EMERGENCY PROCEDURES

NONE APPLICABLE TO THIS AIRPLANE

WEIGHT AND BALANCE

CHEROKEE CRUISER

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/

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THIS SECTION IS NOT

APPLICABLE TO THIS AIRPLANE

OPERATING

,',

CHEROKEE CRUISER

OPERA TlNG INSTRUCTIONS

PREFLIGHT

OPERATING INSTRUCTIONS

REVISED: JULY 13, 1984

OPERATING TIPS

±

PERFORMANCE CHARTS

CHEROKEE

I

I I

THIS CHART SHOULD BE USED TO

DETERMINE DENSITY ALTITUDE

FROM EXISTING TEMPERATURE

AND PRESSURE ALTITUDE CONDITIONS

FOR USE WITH PERFORMANCE CHARTS.

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TEMPERATURE.

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FLAPS 0°

PAVED LEVEL DRY RUNWAY

FULL POWER BEFORE BRAKE RELEASE

ZERO WIND

EXTRAPOLATION OF CHART ABOVE 7000 FT. IS ItVAUO-

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GROSS WEIGHT

1950

--- 2150

LBS.

LBS.

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