Piper CHEROKEE CRUISER PA-28-140 Quick setup guide

THE
PILOT’S OPERATING MANUAL
This manual is incomplete without an APPROPRIATE FAA APPROVED AIRPLANE
FLIGHT MANUAL and an APPROPRIATE WEIGHT AND BALANCE REPORT.
BY
REFERENCE ONLY
THIS ELECTRONIC VERSION
OF THE POM/AFM IS
NOT APPROVED TO
REPLACE ANY OPERATING
INFORMATION REQUIRED
BY THE REGULATIONS.

ii
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
AIRCRAFT SERIAL
NO. _______ REGISTRATION NO. ___ _
PILOT'S OPERATING MANUAL, PART NUMBER 761 555 REVISION
____ _
PIPER AIRCRAFT CORPORATION
APPROVALSIGNATUREANDSTAMP
_________________________ __
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 FAA, ~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

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 Description Date
Pages
Rev. I - 761 555 1-1
Changed Instructional Power Cruise Speed Oct. 22, 1973
(PR731022) from 50% to 60%.
W/B
Added Rev. 1 to Report: VB-546.
9-4 Added "Best Economy Mixture".
9-5 Revised type size.
9-6 Removed NOTE.
9-7 Removed NOTE.
Rev. 2 - 761 555
11 Added PAC Approval Form. May 29, 1974
(PR740529) iii Added Applicability and Item III. Original
Pages Issued.
AF/M
Added Rev. [ to Report: VB-557.
W/B
Added Rev. 2 to Report: VB-546.
(NOTE: AIRCRAFT DELIVERED WITH
MANUALS PRIOR TO THIS REVISION
DO NOT REQUIRE THIS REVISION.)
Rev. 3 -
761 555 Title Added Flite Liner. June
13,1974
(PR740613) 2-1
Added reference to Flite Liner to The
Airplane; relocate info to page 2-2.
2-2 Added info from page
2-1 .
2-8 Added annunciator panel info and foot -
note; relocated info to page 2-11.
2-9 Revised Alternator and Starter Schematic.
2-9a Added page (Alternator and Starter
Schematic).
2-10 Relocated page.
2-11 Relocated page; added info from page 2-8;
added annunciator panel to Vacuum System
and Instrument Panel; added footnote.
2-12 Relocated page; added annunciator panel.
2-12a Added page.
AF/M
Added Rev. 2 to Report: VB-557.
4-6 Revised Alternator Failure, item 3.
W/B
Added Rev. 3 to Report: VB-546.
7-i Added Airspeed Data and revised page nos.
7-4 Added annunciator panel and footnote.
7-5 Revised Stall info; deleted stall table;
added Cruising info from page 7-6; revised
Cruising info; revised stall info.
7-6 Relocate Cruising to page 7-5; added
Approach-and Landing info from page 7-7.
iv

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)
Revision Revised Description Date
Pages
Rev. 3 (cont) 7-7 Added Airspeed Data; relocated Approach
and Landing info to page 7-6.
8-1
Revised item 6. (added annunciator);
added footnote; relocated info from item
8.
to page 8-2.
8-2 Added info from page 8-1.
9-i Revised chart nomenclature.
9-2 Revised Takeoff chart.
9-3 Revised Climb chart.
9-4 Revised Power chart.
9-5 Revised Cruise chart.
9-6 Revised Range chart (36 gal).
9-7 Revised Range chart (50 gal).
9-8 Revised Glide chart.
9-9 Revised Stall chart (weight).
9-10 Revised Stall chart (angle
of bank).
9-11
Revised Landing chart.
Rev. 4 - 761 555 1-2
Revised footnote. Nov.
1,1974
(PR7411Ol)
AF/M Added Rev. 3 to Report: VB-557.
W/B
Added Rev. 4 to Report: VB-546.
7-4 Added new item 9. and revised existing
item nos. under Takeoff.
8-2 Added item
11.
Rev. 5 - 761 555 2-16 Revised Stall Warning description. Jan. 21, 1975
(PR750121)
W/B Added Rev. 5 to Report: VB-546.
7-10 Revised Operating Instructions for Emergency
Locator Transmitter; relocated material to
page
7-1l.
7-11
Added material relocated from page 7-10.
Rev. 6 - 761 555 1-2 Revised Empty Weight and Useful Load. May
16, 1975
(PR750516
W/B
Added Rev. 6 to Report: VB-546.
8-1
Relocated item 8. (fuel tip) to page 8-2.
8-2 Added and revised item
8. (fuel tip).
Rev. 7 -
761 555
2-1
Deleted info (AIRFRAME). July
18, 1975
(PR750718) 2-10 Added callout.
2-12 Added Engine Hour Meter; revised
callouts.
W/B Added Rev. 7 to Report: VB-546.
iv-a

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)
Revision Revised Description Date
Pages
Rev. 8 - 761 555
AF/M
Added Rev. 4 to Report: VB-557. Nov. 27, 1975
(PR751127)
WIB
Added Rev. 8 to Report: VB-546.
7-11
Revised ELT info.
8-2 Revised item
8.
Rev. 9 - 761 555 1-2 Revised Fuel Specifications. April
19, 1976
(PR760419)
AF/M
Added Rev. 5 to Report: VB-557.
7-4 Added Note.
7-5 Revised Cruising Info.
7-6 Revised Approach and Landing item
2.
8-2 Added items 12, 13,
14.
lO-i
Revised page nos. for Filling Fuel Tanks,
Draining Fuel Valves and Lines, Facts
You
Should Know, and Required Service and
Inspection Periods.
10-8 Revised Fuel Requirements; relocated
Filling Fuel Tanks to page 10-9.
10-9 Added Fuel Grade Comparison Chart and
info from page 10-8; relocated Draining
Fuel Valves and Lines to page 10-10.
10-10 Added info from page 10-9 and relocated
Facts
You Should Know to page 10-11.
10- 11
Added info from page 10-10 and relocated
info to page 10-12.
10-12 Added info from page
10-11 and relocated
info to page 10-13.
10-13 Added info from page 10-12.
10-14 Revised Special Instruction
No.7.
Rev. 10 - 761 555
W/B
Added Rev. 9 to Report: VB-546. July
19, 1976
(PR760719) 7-10 Added info from page 7-11. Deleted info
about Emergency Locator Transmitter.
7-11
Moved info to page 7-10; revised pilot's
remote switch description.
Rev.
11 - 761 555 7-2 Revised Starting Engines When Hot. June
3,1977
(PR770603)
7-11
Revised ELT Note.
Rev. 12 - 761 555 ...
III
Added Applicable Serial Numbers. Sept. 30, 1977
(PR770930)
AF/M
Added Rev. 6 to Report: VB-557.
W/B
Added Rev. 10 to Report: VB-546.
(NOTE: AIRCRAFT DELIVERED WITH
MANUALS PRIOR TO THIS REVISION
DO NOT REQUIRE THIS REVISION.)
iv-b

PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)
Revision Revised Description Date
Pages
Rev. 13 - 761 555 2-8 Added Warning. April 16, 1979
(PR790416) 2-14 Added Caution.
W/B Added Rev. 11 to Report: VB-546.
7-10 Revised ELT info.
10-10 Added Caution; relocated info. to pg. 10-11.
10-11 Added info. from pg. 10-10.
Rev. 14 -761 555 2-8 Revised Warning. May
22,1980
(PR800522)
W/B Added Rev.12 to Report: VB-546.
Rev.
15 -761 555 l-i
Revised General Specifications. July 13, 1984
(PR840713) 1-2 Relocated Dimensions
to pg. 1-3:
revised fuel and Oil specification.
1-3 Added Dimensions from pg. 1-2.
2-6 Revised fuel info.
AF/M Added Rev. 7 to Report: VB-557.
W/B
Added Rev. 13 to Report: VB-546.
7-1
Revised Preflight.
7-4, Added ending serial number effectivity.
8-1
9-i Added Warning.
10-8 Revised Fuel Requirements.
10-11 Revised Handling and Servicing (Facts
You Should Know).
10-12 Revised Preventive Maintenance.
10-13 Deleted Preventive Maintenance info.;
revised Required Service and Inspection
Periods.
Rev. 16 - 761 555 iv-c Added Rev.
16 to 761 555 Log of Revisions. March 16, 1990
(PR900316) 10-8 Revised Oil Requirements. Moved Fuel
System to page 10-8a.
10-8a Added page. Revised and moved Fuel System
from page 10-8.
10-8b Added page.
10-9 Revised Fuel Grade Comparison Chart.
10-11 Revised Handling and Servicing (Facts
You Should Know).
10-13 Revised Required Service and Inspection
Periods.
iv-c

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
v

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)
800
1700
89
631
78
142*
135*
10,950
13,000
127
114
705
765
855
126
120
114
720
795
880
124
110
475
(675***)
540
(760***)
*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
OIL
AVGAS ONLY
Fuel Capacity (U.S. gal) Standard
Fuel Capacity (U.S. gal) Reserve
Fuel, Aviation Grade
Minimum Octane
Specified Octane
Alternate Fuels
Oil Capacity (quarts)
BAGGAGE
Maximum Baggage (Ibs)
Baggage Space (cubic
ft)
8.4
5.6
55
535
2150
1275
875
0-320-E3D
150 at 2700
5.125
3.875
319.8
7: 1
276
8
M74DM
36
50
80/87
80/87
Refer to Fuel Requirements,
Section
10 -Page 10-8
8
200*
22
*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)
GENERAL SPECIFICATIONS
REVISED: JULY 13, 1984
CHEROKEE CRUISER
30
160
13.4
23.3
7.3
14.3
6.2
10.0
24
24
6.00 x 6
6.00 x 6
1-3

CHEROKEE CRUISER
0"
63.75"--1
+-----10'---~
~-------- 23' 5.4" -----/
1-4
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
2
-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

\:
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~~---, ----
AIRPLANE AND SYSTEMS
ISSUED: JULY 6, 1973
Main Wheel Assembly
CHEROKEE CRUISER
2-3

CHEROKEE CRUISER
2-4
Throttle Quadrant and Console
AIRPLANE AND SYSTEMS
ISSUED: JULY 6,1973