Piper CHEROKEE 180 User guide

CHEROKEE 180
PA-28-180
owner's Handbook
Piper Aircraft Corporation, Vero Beach, Florida
U.5. A.

NOTICE
THIS HANDBOOK IS NOT DESIGNED, NOR CAN ANY
HANDBOOK SERVE, AS A SUBSTITUTE FOR ADEQÚATE AND
COMPETENT FLIGHT INSTRÚCTION, 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 THAN IS PERMISSIBLE TO SET FORTH IN
TI-iE AIRPLANE FLIGHT MANUAL.
IF THERE IS ANY INCONSIS'i'ENCY BETWEEN THIS
HANDBOOK AND THE AIRPLANE PLIGHT MANUAL APPROVED
BY THE F.A.A., THE FLIGHT MANUAL SHALL GOVERN.
Revised text and illustrations shall be indicated by a
black vertical lirm in the margin opposite the change.
Additional copies of this manual, Part No. 761 513,
may be obtained from your Piper Dealer.
Published by
PUBLICATIONS DEPARTMENT
Piper Aircraft Corporation
761 513
Issued: June 1972
Revised: January 1973

SECTION 1
SPECIFICATIONS
Performance .................... .......... 1
Weights ............ ...... ......... 2
PowerPlant.................... ......... 2
FuelandOil ................... ........... 2
Baggage ................... ... ......... 2
Dimensions ................................ 3
LandingGear............. .. ... ......... 3

CHEROKEE 180 SECTION I
SECTION I
SPECIFICATIONS
PERFORMANCE
Performance figures are for airplanes equipped for cross-country
transportation and flown at gross weight under standard conditions at
sea level or stated altitude. Any changes in equipment may result in
changes in performance.
Take-off Ground Run (S.L. Std., maximum effort, 25 °
flap) (ft) 720
Take-off over 50-ft Barrier S.L. Std., (maximum effort,
25°flap) (ft) 1625
Best Rate of Climb Speed (mph) 85
Rate of Climb (ft per min) 725
Service Ceiling (ft) 14,150
Absolute Ceiling (ft) 16,500
Top Speed (mph) 148
Optimum Cruise Speed (TAS) (75% power,
optimum altitude, leaned to best power) (mph) 141
Cruising Range (75% power, optimum altitude
leaned to best economy, no reserves or climb
allowance) (mi) 686
Optimum Cruising Range (55% power, 10,000 ft,
leaned to best economy, no reserves or climb
allowance (mi) 706
Stalling Speed CAS (flaps down) (mph) 61
-Stalling Speed CAS (flaps up) (mph) 68
Landing Roll S.L. Std., (flaps down) (ft) 635*
Landing Roll over 50-ft Barrier S.L. Std., (ft) 1185*
*This value applies only for the conditions indicated on the landing
distance versus density altitude chart.
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SECTION ICHEROKEE 180
SPECIFICATIONS (cont.)
WEIGHTS
Gross Weight (lbs) 2450
Empty Weight (Standard) (lbs) 1384*
USEFUL LOAD (Standard) (lbs) 1066*
POWER PLANT
Engine (Lycoming) O-360-A4A
Rated Horsepower 180
Rated Speed (rpm) 2700
Bore (in.) 5.125
Stroke (in.) 4.375
Displacement (cu in.) 361.0
Compression Ratio 8.5:1
Dry Weight (lbs) 285
Propeller 76EM8S5-0-60
FUEL AND OIL
Fuel Capacity (U.S. gal) Usable 48
Oil Capacity (qts) 8
Fuel, Aviation Grade (min octane) 100/130
BAGGAGE
Maximum Baggage (lbs) 200
Baggage Space (cu ft) 24
Baggage Door Size (in.) 20 x22
*Weight varies with each aircraft
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CHEROKEE 180 SECTION I
SPECIFICATIONS (cont.)
DIMENSIONS
Wing Span (ft) 32
Wing Area (sq ft) 170
Wing Loading (lbs per sq ft) 14.4
Length (ft) 24.0
Height (ft) 7.8
Power Loading (lbs per hp) 13.6
LANDING GEAR
Wheel Base (ft) 6.7
Wheel Tread (ft) 10
Tire Pressure (psi) Nose 24
Main 24
Tire Size Nose (4 ply rating) 6.00 x6
Main (4 ply rating) 6.00 x6
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SECTION ICHEROKEE 180
50"
3"
2.50"
10'
-24' 09"
T.ß0"
---8' 8.4"
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SECTION 11
DESIGN INFORMATION
EngineandPropeller ............ .. ......... 5
Structures.......... ..... .... .......... 5
LandingGear ........... ... ............ 6
ControlSystems ......... .... ........ 7
FuelSystem ........ ....... 7
Electrical System . . . ... . . . . .. . .. . . . . . 9
Heating and Ventilating System .... . . . ...... . .. . .13
CabinFeatures .......... . . ........ 13
Optional Equipment .... . . . . . ..... . . . 16

CHEROKEE 180 SECTION 11
SECTION 11
DESIGN INFORMATION
ENGINE AND PROPELLER
The Cherokee 180 is powered by a Lycoming O-360-A4A four
cylinder, direct drive, horizontally opposed engine rated at 180 HP at
2700 RPM. It is furnished with a starter, 60 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. Aheater shroud around the
mufflers is provided to supply heat for the cabin and windshield
defrosting.
The Sensenich 76EM8S5-0-60 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 lacquer.
The wings are attached to each side of the fuselage by inserting the
butt ends of the respective main spars into aspar 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.
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SECTION Il CHEROKEE 180
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.
LANDING GEAR
The three landing gears use aCleveland 6.00 x6wheel, the main
wheels being provided with Cleveland single disc hydraulic brake
assemblies, No. 30-55. All wheels use 6.00 x6four ply tires with tubes.
The nose gear is steerable through a44 degree are by use of the
rudder pedals. Aspring 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 ahydraulic
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.
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CHEROKEE 180 SECTION II
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 atrim tab mounted on the
trailing edge of the stabilator to reduce the control system forces. This
tab is actuated by a control wheel on the floor between the front seats.
The stabilator provides extra stability and controllability with less size,
drag and weight than conventional tail surfaces. The ailerons are
provided with adifferential 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
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. Apast-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 astep 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 (24 gal. usable) 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 fuel selector control is located on the left side-panel, forward
of the pilot's seat. The button on the selector 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.
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.
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SECTION II CHEROKEE 180
FUEL
PRESSURE
GAUGE
FUELQUANTITY
GAUGES
ENGINEFUELPUMP
litt rÎr
DRAIN
ELPUMP
VENT
SASCOLATOR
FUEL
SELECTOR
VALVE
VENT
LEFT
TANK __, RIGHTTANK
UU
DRAIN ORAIN
FUEL SYSTEMSCHEMATIC
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CHEROKEE 180 SECTION II
Each tank has an individual quick drain loacated 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 aquick 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. 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.
Fuel quantity and pressure are indicated on gauges located in a
cluster on the left side of the instrument panel.
ELECTRICAL SYSTEM
The electrical system includes a12 volt 60 amp alternator, battery,
voltage regulator, overvoltage relay and master switch relay. The
battery is mounted in a stainless steel box immediately aft of the
baggage compartment. The regulator and overvoltage relay are located
on the forward left side of the fuselage behind the instrument panel.
Electrical switches are located on the right center instrument panel,
and the circuit breakers are located on the lower right instrument panel.
Arheostat-switch on the left side of the switch panel controls the
navigation lights and the dome instrument light. It also dims the dome
light. The similar switch on the right side controls and dims the panel
lights.
eeeeooooseeee
ALTERNATOR ENGINE FUEL STALL AUTO PITOT TUANS PtTCH START
GUTPUT FIELD IGROUP IPUMP I1 lwAANING I I PILOT HEAT |BANK iTRIM iSACC
oeeeeeeeeeces
INSTRUMENTLIGHT NAV NTi- LANDtNG AV-COM NAV-COM ADF AUDIO AIA DME TRANS
PANEL OVEAHEA LIGHTS LtBHT LlGHTS :2PANEL CONO. PONDER
DOOR REMOVEDFÒR CLARITY
Circuit Breaker Panel
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SECTION II CHEROKEE 180
The alternator system offers many advantages over the generator
system both in operation and maintenance. The main advantage is full
electrical power output at lower engine RPM. This is agreat
improvement for radio and electrical equipment operation. Since the
alternator output is available at all times, the battery will be charging
for agreater percentage of use. This will make cold-morning starting
easier.Standard accessories include astarter, electric fuel pump, stall
warning indicator, cigar lighter, fuel gauge and ammeter. The navigation
lights, anti-collision light, landing light, instrument lighting and cabin
dome light are optional. Circuits will handle an entire complement of
communications and navigational equipment.
The words "master switch" used hereafter in this manual indicate
both sides of the switch, battery side "BAT" and alternator side "ALT"
are to be depressed simultaneously to OFF or ON as directed.
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 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 afully charged battery, will appear
continuously under these flight conditions. The amount of current
shown on the ammeter will tell immediately if the alternator system is
operating normally, as the amount of current shown should equal the
total amperage 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 5ampere field breaker and 60 ampere output breaker and
reset if open. If neither circuit breaker is open, turn off the "ALT"
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.
Maintenance on the alternator should prove to be a minor factor.
Should service be required, contact the local Piper Dealer.
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CHEROKEE 180 SECTION II
HEATING AND VENTILATING SYSTEM
Heat for the cabin interior and the defroster system is provided by
aheater 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.
The air flow can be regulated between the front and rear seats by
levers located on top of the heat ducts next to the console.
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.
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 avacuum 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.
Anatural 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 radios
and circuit breakers located on the right hand instrument panel have
extra circuits provided for acomplete line of optional radio equipment.
The microphone is located on the control quadrant covet, see
illustration page 14, item 42.
The cabin interior includes apilot 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.
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CHEROKEE 180 SECTION II
Asingle strap shoulder harness controlled by an inertia reel is
standard equipment for the front seats, and is offered as an option for
the rear seats. The shoulder strap is routed over the shoulder adjacent
to the windows and attached to the lap belt in the general area of the
person's inboard hip.
A check of the inertia reel mechanism is made by pulling sharply
on the strap. The reel will lock in place under this test and prevent the
strap from extending. Under normal movement the strap will extend
and retract as required.
The 24 cubic foot baggage area may be reached from the cabin or
through a large 20 x22 inch outside door.
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SECTION 11 CHEROKEE 180
AIR CONDITIONING*
The air conditioning system is arecirculating 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 aretractable 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 aflush 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 desired 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.
*Optional Equipment
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CHEROKEE 180 SECTION II
NOTE
If the system is not operating in 5minutes 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 obtain 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.
Acircuit breaker located on the circuit breaker panel protects the
air conditioning electrical system.
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
1/4 inch, the clutch will engage and the scoop will extend, again
supplying cool, dry air.
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SECTION 11 CHEROKEE 180
NOTES
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