Piper CHEROKEE 180 C User guide

PIPER CHEROKEE 180 C
PA-28-180
Owner’s Handbook
Piper Aircraft Corporation, Vero Beach, Florida
U.S.A.

ii
NOTICE
THIS HANDBOOK IS NOT DESIGNED, NOR CAN ANY HANDBOOK SERVE, AS A SUBSTITUTE FOR
ADEQUATE AND COMPETENT FLIGHT INSTRUCTION, OR KNOWLEDGE OF THE CURRENT
AIRWORTHINESS DIRECTIVES, THE APPLICABLE FEDERAL AIR REGULATIONS, AND ADVISORY
CIRCULARS. IT IS NOT INTENDED TO BE A GUIDE OF BASIC FLIGHT INSTRUCTION, NOR A
TRAINING MANUAL.
THE HANDBOOK IS DESIGNED:
1. TO HELP YOU OPERATE YOUR CHEROKEE WITH SAFETY AND CONFIDENCE.
2. TO MORE FULLY ACQUAINT YOU WITH THE BASIC PERFORMANCE AND HANDLING
CHARACTERISTICS OF THE AIRPLANE.
3. TO MORE FULLY EXPLAIN YOUR CHEROKEE’S OPERATION THAT IS PERMISSIBLE TO SET
FORTH IN THE AIRPLANE FLIGHT MANUAL.
IF THERE IS ANY INCONSISTENCY BETWEEN THIS HANDBOOK AND THE AIRPLANE FLIGHT
MANUAL APPROVED BY THE FAA, THE AIRPLANE FLIGHT MANUAL SHALL GOVERN.
___________________________________________________
Revised text and illustrations shall be indicated by a black vertical line in the margin
opposite the change. A line opposite the page number will indicate that material was
relocated.
Additional copies of this manual, Part No. 753 683, may be obtained from your Piper
Dealer.
___________________________________________________
Published by
PUBLICATIONS DEPARTMENT
Piper Aircraft Corporation
753 683
Issued: August 1964
Revised: February 2, 1979
Consolidated Information added: November 2020

iii
INDEX
SECTION I – SPECIFICATIONS
Page
Performance
Weights
Power Plant
Fuel and Oil
Baggage
Dimensions
Landing Gear
1
2
2
2
2
3
3
SECTION II – DESIGN INFORMATION
Page
Engine and Propeller
Structures
Landing Gear
Control Systems
Fuel System
Electrical System
Heating and Ventilating System
Cabin Features
6
6
7
7
8
10
11
13
SECTION III – OPERATING INSTRUCTIONS
Page
Preflight
Starting Engine
Warm-Up
Ground Check
Take-Off
Climb
Stalls
Cruising
Approach and Landing
Stopping Engine
Engine Power Loss
Ground Handling and Mooring
Weight and Balance
Operating Tips
16
17
18
18
19
20
20
20
21
22
23
23
23
23

iv
INDEX (continued)
SECTION IV – EMERGENCY PROCEDURES
Page
Introduction
Engine Power Loss During Takeoff
Engine Power Loss In Flight
Power Off Landing
Fire
Loss of Oil Pressure
Loss of Fuel Pressure
High Oil Temperature
Alternator Failure
Engine Roughness
Spins
Open Door
27
27
28
29
30
31
31
32
32
32
33
34
SECTION V – PERFORMANCE CHARTS
Page
Altitude Conversion Chart
Takeoff Distance vs Density Altitude
Rate of Climb vs Density Altitude
Range vs Density Altitude
True Airspeed and RPM vs Density Altitude
Landing Distance vs Density Altitude
Power Setting Table
36
37
38
39
40
41
42
SECTION VI – GENERAL MAINTENANCE
Page
Landing Gear Service
Brake Service
Tire Inflation
Care of Windshield and Windows
Battery Service
Fuel Requirements
Oil Requirements
Fuel System
Care of Air Filter
Leveling and Rigging
Serial Number Plate
44
45
45
46
46
46
47
48
49
49
50

v
INDEX (continued)
APPENDIX – ORIGINAL PIPER AIRCRAFT FLIGHT MANUAL
Limitations Section
Weight and Balance Section
Current Equipment List Revision (Weight & Balance)

PIPER CHEROKEE 180 “C”
SECTION I
1
SECTION I
SPECIFICATIONS

PIPER CHEROKEE 180 “C”
SECTION I
2
SECTION I
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.
Take-off Run (maximum effort, 25° flap) (ft)
Take
-off over 50-ft barrier (maximum effort, 25° flap) (ft)
Best Rate of Climb Speed (mph)
Rate of Climb (ft per min)
Service Ceiling (ft)
Absolute Ceiling (ft)
Top Speed (mph)
Cruising Speed (75% power,
Sea Level) (mph)
Cruising Range (75% power,
Sea Level) (mi) (hrs)
Cruising Speed
(75% power, 7000 ft altitude) (mph)
Cruising Range (7
5% power, 7000 ft altitude) (mi)
Optimum Cruising R
ange
(55% power, 10,000 ft., std. fuel 7.2 gph)
(mi) (hrs)
Fuel Consumption (75% power) (gph)
Stalling Speed (flaps down) (mph)
Stalling Speed (flaps up) (mph)
Landing Roll (flaps down) (ft)
Landing Roll over 50-ft barrier (ft)
720
1625
85
750
16,400
19,000
152
134
680 | 5 hrs
143
725 | 5 hrs
845 | 6.8 hrs
10
57
67
600
1150

PIPER CHEROKEE 180 “C”
SECTION I
3
WEIGHTS
Gross Weight (lbs)
Empty Weight (Standard) (lbs)
USEFUL LOAD (Standard) (lbs)
2400
1230
1170
POWER PLANT
Engine (Lycoming)
Rated Horsepower
Rated Speed (rpm)
Bore (in.)
Stroke (in.)
Displacement (cu in.)
Compression Ratio
Dry Weight (lbs)
Oil Sump Capacity (qts)
Fuel Aviation Grade
(Minimum Octane)
(Specified Octane)
Propeller
O-360-A3A
180
2700
5.125
4.375
361.0
8.5:1
285
8
91/96
91/96
M76EMMS
FUEL AND OIL
Fuel Capacity (U.S. Gal)
Oil Capacity (qts)
Fuel, Aviation Grade (Minimum Octane)
50
8
91/96
BAGGAGE
Maximum Baggage (lbs)
Baggage Space (cu ft)
Baggage Door Size
200
17
20 x 22

PIPER CHEROKEE 180 “C”
SECTION I
4
DIMENSIONS
Wing Span (ft)
Wing Area (sq ft)
Wing Loading (lbs per sq ft)
Length (ft)
Height (ft)
Power Loading (lbs per hp)
30
160
15.0
23.5
7.3
13.3
LANDING GEAR
Wheel Base (ft)
Wheel Tread (ft)
Tire Pressure (psi) Nose
Main
Tire Size Nose (4 ply rating)
Main (4 ply rating)
6.2
10
24
24
6.00 x 6
6.00 x 6
LANDING GEAR
Wheel Base (ft)
Wheel Tread (ft)
Tire Pressure (psi) Nose
Main
Tire Size Nose (4 ply rating)
Main (4 ply rating)
6.2
10
24
24
6.00 x 6
6.00 x 6

PIPER CHEROKEE 180 “C”
SECTION I
5

PIPER CHEROKEE 180 “C”
SECTION II
5
SECTION II
DESIGN INFORMATION

PIPER CHEROKEE 180 “C”
SECTION II
6
SECTION II
DESIGN INFORMATION
ENGINE AND PROPELLER
The Piper Cherokee 180 “C” is powered by a Lycoming O-360-A3A four
cylinder, direct drive, horizontally opposed engine rated at 180 HP at 2700
RPM. It is furnished with a starter, 35 ampere 12 volt alternator, shielded
ignition, vacuum pump drive, fuel pump, and a dry, automotive type
carburetor air filter.
The exhaust system is of the cross-over type to reduce back pressure and
improve performance. It is made entirely from stainless steel and is equipped
with dual mufflers. A heater shroud around the mufflers is provided to supply
heat for the cabin and windshield defrosting.
The Sensenich M76EMMS fixed-pitch propeller is made from a one-piece alloy
forging.
STRUCTURES
All structures are of aluminum alloy construction and are designed to ultimate
load factors well in excess of normal requirements. All exterior surfaces are
primed with etching primer and painted with acrylic enamel.
The wings are attached to each side of the fuselage by inserting the butt ends
of the respective main spars into a spar box carry-through which is an integral
part of the fuselage structure, providing in effect a continuous main spar with
splices at each side of the fuselage. There are also fore and aft attachments at
the rear spar and at an auxiliary front spar.
The wing airfoil section is a laminar flow type, NACA652-415 with the
maximum thickness about 40% aft of the leading edge. This permits the main
spar carry-through structure to be located under the rear seat providing
unobstructed cabin floor space ahead of the rear seat.

PIPER CHEROKEE 180 “C”
SECTION II
7
LANDING GEAR
The three landing gears use a Cleveland 6.00 x 6 wheel, the main wheels being
provided with Cleveland single disc hydraulic brake assemblies, No. 30-55. All
wheels use 6.00 x 6 four ply tires with tubes.
The nose gear is steerable through a 30 degree arc by use of the rudder
pedals. A spring device is incorporated in the rudder pedal torque tube
assembly to aid in rudder centering and to provide rudder trim. The nose gear
steering mechanism also incorporates a hydraulic shimmy dampener.
The three struts are of the air-oil type, with the normal extension being 3.25
inches for the nose gear and 4.50 inches for the main gear.
The standard brake system for the Cherokee consists of a hand lever and
master cylinder which is located below and behind the left center of the
instrument sub-panel. The brake fluid reservoir is installed on the top left front
face of the firewall.
The parking brake is incorporated in the master cylinder and is actuated by
pulling back on the brake lever, depressing the knob attached to the handle
and releasing the brake lever. To release the parking brake, pull back on the
lever to disengage the catch mechanism and allow the handle to swing
forward.
Optional toe brakes are available to supplement the standard hand lever and
parking brake system.
CONTROL SYSTEMS
Dual controls are provided as standard equipment with a cable system used
between the controls and the surfaces. The horizontal tail is of the Flying Tail
type (stabilator), with an anti-servo tab which also acts as a longitudinal trim
tab, actuated by a control on the cabin ceiling. The stabilator provides extra
stability and controllability with less size, drag and weight than conventional
tail surfaces. The ailerons are provided with a differential action which tends
to reduce adverse yaw in turning maneuvers, and which also reduces the
amount of coordination required in normal turns. A rudder trim adjustment is

PIPER CHEROKEE 180 “C”
SECTION II
8
mounted on the right side of the pedestal below the throttle quadrant and
permits directional trim as needed in flight.
The flaps are manually operated, balanced for light operating forces and
spring-loaded to return to the up position. A past center lock incorporated in
the actuating linkage holds the flap when it is in the up position so that it may
be used as a step on the right side. The flap will not support a step load except
when in the full up position, so it must be completely retracted when used as a
step. The flaps have three extended positions: 10, 25 and 40 degrees.
FUEL SYSTEM
Fuel is stored in two 25 gallon tanks which are secured to the leading edge
structure of each wing by screws and nut plates. This allows easy removal for
service or inspection.
The standard quantity of fuel is 50 gallons for the Cherokee 180. Each tank is
fitted with a filler neck indicator, which extends some distance into the tanks.
Filling the fuel tanks to the bottom of the indicator will provide approximately
36 gallons of fuel (18 gal per tank).
An auxiliary electric fuel pump is provided in case of failure of the engine-
driven pump. The electric pump should be on for all take-offs and landings,
and when switching tanks. The pump switch is located in the switch panel
above the throttle quadrant. Each tank has an individual quick drain located at
the bottom, inboard rear corner, and should be drained to check for water
before each flight. The fuel strainer, which is also equipped with a quick drain,
is located on the front lower left corner of the firewall. This strainer should be
drained regularly to check for water or sediment accumulation.
Fuel quantity and pressure are indicated on gauges located in a cluster on the
left side of the instrument panel.

PIPER CHEROKEE 180 “C”
SECTION II
9

PIPER CHEROKEE 180 “C”
SECTION II
10
ELECTRICAL SYSTEM
The electrical system includes a 12 volt alternator, battery, voltage regulator
and master switch relay. The battery, regulator and relay are mounted in a
stainless steel box immediately aft of the baggage compartment. Access for
service or inspection is conveniently obtained through a removable panel at
lower right corner of the compartment.
Electrical switches, fuses and fuse spares are located on the lower left center
of the instrument panel, and the left side of the instrument sub-panel.
Standard electrical accessories include: Starter, Electric Fuel Pump, Fuel
Gauge, Stall Warning Indicator, Cigar Lighter and Ammeter.
Navigation Lights, Anti-Collision Light, Landing Light, Instrument Lighting and
Cabin Dome Light are offered as Optional accessories.
Circuit provisions are made to handle optional communications and
navigational equipment.
Installed on the Cherokee is the F.T.P. (Full Time Power) electrical system.
Derived from the system are many advantages both in operation and
maintenance. The main advantage is, of course, full electrical power output
regardless of engine R.P.M. This is a great improvement for radio and
electrical equipment operation. Also because of the availability of generator
out-put at all times, the battery will be charging for a greater percentage of
use, which will greatly improve cold-morning starting.
Unlike previous generator systems, the ammeter does not indicate battery
discharge; rather it displays in amperes the load placed on the alternator.
With all electrical equipment off (except the master switch) the ammeter will
be indicating the amount of charging current demanded by the battery. As
each item of electrical equipment is turned on, the current will increase to a
total appearing on the ammeter. This total includes the battery. The
maximum continuous load for night flight, with radios on is about 30 amperes.
This 30 ampere value, plus approximately two amperes for a fully charged
battery, will appear continuously under these flight conditions. The amount of

PIPER CHEROKEE 180 “C”
SECTION II
11
current shown on the ammeter will tell immediately whether the alternator
system is operating normally, as the amount of current shown should be equal
to the total amount of amperes being drawn by the equipment which is
operating.
If no output is indicated on the ammeter during flight, reduce the electrical
load by turning off all unnecessary electrical equipment. Check both 5 ampere
field breaker and 60 ampere output breaker and reset if open. If neither
circuit breaker is open, turn off the master switch for 30 seconds to reset the
overvoltage relay. If ammeter continues to indicate no output, maintain
minimum electrical load and terminate flight as soon as practical.
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.
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. Cabin air is exhausted
through an outlet located below the rear seat.

PIPER CHEROKEE 180 “C”
SECTION II
12

PIPER CHEROKEE 180 “C”
SECTION II
13
PIPER CHEROKEE 180 – ELECTRICAL SYSTEM

PIPER CHEROKEE 180 “C”
SECTION II
14
CABIN FEATURES
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. Above the Attitude Gyro are two
lights which indicate high or low vacuum. A natural separation of the flight
group and the power group is provided by placing the flight group in the upper
instrument panel and the power group in the center and lower instrument
panels.
The cabin interior includes a pilot storm window, two sun visors, ash trays, two
map pockets, and pockets on the backs of each front seat. The front seats are
adjustable fore and aft for pilot-passenger comfort and ease of entry and exit.
Arm rests are also provided for the front seats. The 24 cubic foot baggage area
may be reached from the cabin or through a large 20 x 22 inch outside door.