Piper CHEROKEE D User guide

CHEROKEE D
PA-28-180
Owner's Handbook
Piper Aircraft Corporation, Vero Beach, Florida
U.S. A.

NOTICE
THIS HANDBOOK
IS NOT DESIGNED, NOR CAN ANY
HANDBOOK SERVE, AS A SUBSTITUTE
FOR ADEQUATE AND
COMPETENT FLIGHT
INSTRUCfiON, OR KNOWLEDGE OF THE
CURRENT AIRWORTHINESS DIRECfiVES, 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 CHARACfERISTICS
OF THE AIRPLANE.
3.
TO MORE FULLY EXPLAIN YOUR CHEROKEE'S
OPERATION THAN
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 F.A.A., THE FLIGHT MANUAL SHAI.L GOVERN.
Revised text and illustra;tions shall be indicated by a
black vertical line in the margin opposite the change.
Additional copies of this manual, Part No. 753 765
may be obtained from your Piper Pealer.
Published by
PUBLICATIONS DEPARTMENT
Piper Aircraft Corporation
753 765
Issued: November 1967
Revised: January 1973 ·

Performance
Weights. .
Power Plant
Fuel and Oil
Baggage
Dimensions
Landing Gear .
671101
SECTION I
SPECIFICATIONS
1
2
2
2
2
3
3

CHEROKEE "D"
SECTION I
SECTION I
SPECIFICATIONS
PERFORMANCE
Performance figures are fcir airplanes equipped for cross-
country transportation and flown at gross weight under standard
conditions at sea level or stated altitude. Any changes in equip-
ment may result in changes in performance.
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)
Optimum
Cruising Speed (75% power, optimum
altitude) (mph)
Cruising Range (75% power, optimum altitude) (mi)
Optimum
Cruising Range (55% power, optimum
altitude) (mi)
Stalling Speed (flaps down) (mph)
Stalling Speed (flaps up) (mph)
Landing Roll (flaps down) (ft)
Landing Roll over 50-ft barrier (ft)
681115
720
1625
85
750
13,000
15,000
152
143
725
845
57
67
600
1150

SECTION I
SPECIFICATIONS (c:ont}:
WEIGHTS
Gross Weight (lbs)
Empty Weight (Standard) (lbs)
USEFUL LOAD (Standard) (lbs)
POWER PLANT
Engine (Lycoming)
Rated Horsepower
Rated Speed (rpm)
Bore (in.)
Stroke (in.)
Displacement (cu in.)
Compression Ratio
Dry Weight (lbs)
Pro "Peller
FUEL AND OIL
Fuel Capacity '(U.s; gal)
Oil Capacity (qts)
Fuel, Aviation Grade (min octane)
BAGGAGE
2
Maximum Baggage (lbs)
Baggage Space (cu ft)
Baggage Door Size (in.)
CHEROKEE "D"
2400
1294
1106
0-360-MA
180
2700
5.125
4.375
361.0
8.5:1
285
M76EMMS60
so
8
91/96
200
17
20 X 22
671101

CHEROKEE
~·o"
SPECIFICATIONS
(cont):
DIMENSIONS
Wing
Span
(ft)
Wing
Area
(sq
ft)
Wing
Loading
(lbs
per
sq
ft)
Length
(ft)
Height
(ft)
Power
Loading
(lbs
per
hp)
LANDING
GEAR
Wheel
Base
(ft)
Wheel
Tread
(ft)
Tire
Pressure
(psi)
Nose
Main
Tire
Size
671101
Nose
(4
ply
rating)
Main (4 ply
rating)
SECTION
I
30
160
15.0
23.5
7.3
13.3
6.2
10
24
24
6.00
X
6
6.00
X
6
3

SECTION I CHEROKEE "D"
1+------------30'--------_,
4
671101

SECTION II
DESIGN INFORMATION
Engine and Propeller
Structures .
Landing Gear .
Control Systems
Fuel System .
Electrical System
Heating and Ventilating System
Cabin Features .
671101
5
5
6
7
7
9
13
13

CHEROKEE "D"
SECTION II
SECTION II
DESIGN INFORMATION
ENGINE
AND PROPELLER
The Cherokee ''D" is powered by a Lycoming 0-360-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 stain-
less 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 M76EMMS60 fixed-pitch propeller is made
from a one-piece alloy forging.
STRUCTURES
All structures are of aluminum alloy construction and are
designed to ultima:te load factors well in excess of normal re-
quirements. All exterior surfaces are primed with etching primer
and
painted with acrylic enamel.
The wings are attached to each side of the fuselage by in-
serting 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
671101
5

SECTION
II
CHEROKEE
"D"
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.
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 44
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
in-
corporates
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
••
uid
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.
6
671101

CHEROKEE "D"
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 a trim
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 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 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 twenty-five 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 fuel selector control is located on the left side-panel, forward
of the pilot's seat. If a modified selector valve cover has been installed,
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 into the ON_position.
An
auxiliary electric fuel pump is provided in case of failure
730130
7

SECTION. II
FUEl PRESSURE GAUGE
DRAIN
lEFT TANK ·
ORA IN
CARBURETOR
CHEROKEE "D"
ENGINE FUEl PUMP
VENT
RIGHT TANK
ORA IN
FUEL SYSTEM SCHEMATIC
8
671101

CHEROKEE
"D"
SECTION
II
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.
ELECTRICAL
SYSTEM
The
electrical
system
includes
a 12
volt
60
amp
alternator,
battery,
voltage
regulator,
overvoltage
relay
and
master
switch
relay.
The
battery
is
mounted in a
stainless
steel
box
imme-
diately
aft
of
the
baggage
compartment.
The
regulator
and
over-
voltage
relay
are
located
on
the
forward
left
side
of
the
fuselage
behind
the
instrument
panel.
Electrical
switches
are
located
on
the
right
center
instru-
ment
pane
1,
and
the
circuit
breakers
are
located
on
the
lower
right
instrument
pane
1.
A
rheostat
switch
on
the
left
side
of
the
switch
panel
controls
the
navigation
lights
and
the
dome
instru-
ment
light.
It
also
dims
the
dome
light.
The
similar
switch
on
the
right
side
controls
and
dims
the
panel
lights.
~··.
i®®l@l®l
0
1°1®1®1®1®1@1®1®
:~.
ALTERNATOR
ENGINE
FUEL
STALL
GYRO
AUTO
Pi
TOT TURN
6:
PITCH START
;}
OUTPUT FIELD GROUP
PUMP
WARNING
WARNING
PILOT HEAT BANK TRIM
6.
ACC
."/•
.·;·
.:c@)@)@
(@
®1@1@1@1@1@1°1°1°
~
INSTRUMENT
LIGHTSI
NAV
I
ROTATING
I
LANDING NAY-COM NAY-COM ADF
AUDIO
MARKER
· PANEL OVERHEAD LIGHTS BEACON LIGHTS I 2 AMPLIFIER BEACON
.
Circuit
Breaker
Panel
730130
9

SECTION II CHEROKEE
"D"
Standard accessories include a starter, electric fuel pump,
stall warning indicator, cigar lighter,fuel gaugeand 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 equip-
ment.
The alternator system offers many advantages over the gen-
erator system both in operation and maintenance. The main ad-
vantage is full electrical power output at lower engine RPM.
This is a great improvement for radio and electrical equipment
operation. Since the alternator output is available at all times,
the battery will be charging for a greater percentage of use. This
will make cold-morning starting easier.
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 elec-
trical 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 am-
peres for a fully 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 equip-
ment. 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 mini-
mum electrical load and terminate flight as soon as practical.
Maintenance on the alternator should prove to be a minor
factor. Should service be required,'contactthe local Piper Dealer.
10
680415

CHEROKEE "D"
It
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':"' -::-
FUEL TANK SENDERS
671101
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ALTERNATER OUTPUT GD
CIRCUIT PROTECTOR
<!§
~
~
ALTERNATOR FIELD
CIRCUIT PROTECTOR
RADIO
INTERFERENCE CAPACITOR
SECTION II
I CABIN
lUTE
MASTER
SOLENOID
r--------,
d;±.O---------i:-0-'\ . :
"-------r
ELECTRICAL SYSTEM
11

SECTION
II
/
/ /
/
/
2
HEATING
AND
VENTILATING
SYSTEM
12
K
\
5
CHEROKEE
"D"
+
Fresh
Air
Q
Cabin
Heat
1.
Fresh
Air
Control
4.
Defroster
Air
Outlet
2.
Defroster
Control
5.
Fresh
Air
Inlet
3.
Heater
Control
6.
Cabin
Exhaust
Outlet
671101