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Piper Lance II User Manual
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LANCE
II
SERVICE
MANUAL
2-62.
OIL
FILTER.
(FULL
FLOW.)
a.
The
oil
filter
element
should
be
replaced
after
each
50
hours
of
engine
operation;
this
is
accomplished
by
removing
the
lockwire
from
the
bolt-head
at
the
end
of
the
filter
housing,
loosening
the
bolt,
and
removing
the
filter
assembly
from
the
adapter.
b.
Before
discarding
the
filter
element,
remove
the
outer
perforated
paper
cover,
using
a
sharp
knife,
cut
through
the
folds
of
the
element
at
both
ends,
close
to
the
metal
caps.
Then,
carefully
unfold
the
pleated
element
and
examine
the
meterial
trapped
in
the
filter
for
evidence
of
internal
engine
damage
such
as
chips
or
particles
from
bearings.
In
new
or
newly
overhauled
engines,
some
small
particle
of
metallic
shavings
might
be
found;
these
are
generally
of
no
consequence
and
should
not
be
confused
with
particles
produced
by
impacting,
abrasion
or
pressure.
Evidence
of
internal
engine
damage
found
in
the
oil
filter
justifies
further
examination
to
determine
the
cause.
c.
After
the
element
has
been
replaced,
tighten
the
attaching
bolt
within
20
to
25
foot
pounds
of
torque.
Lockwire
the
bolt
through
the
loops
on
the
side
of
the
housing
to
the
drilled
head
of
the
thermostatic
valve.
Be
sure
the
lockwire
is
replaced
at
both
the
attaching
bolt
head
and
the
thermostatic
oil
cooler
bypass
valve.
2-63.
RECOMMENDATIONS
FOR
CHANGING
OIL.:(Refer
to
latest
revision
of
Lycoming
Service
Instruction
No.
1014.)
a.
In
engines
that
have
been
operating
on
straight
mineral
oil
for
several
hundred
hours.
a
change
to
additive
oil
should
be
made
with
a
degree
of
caution,
since
the
cleaning
action
of
some
additive
oils
will
tend
to
loosen
sludge
deposits
and
cause
plugged
oil
passages.
When
an
engine
has
been
operating
on
straight
mineral
oil
and
is
known
to
be
in
excessively
dirty
condition.
the
switch
to
additive
or
compounded
oil
should
be
deferred
until
after
the
engine
is
overhauled.
b.
When
changing
from
straight
mineral
oil
to
compounded
oil,
the
following
precautionary
steps
should
be
taken:
1.
Do
not
add
additive
oil
to
straight
mineral
oil.
Drain
the
straight
mineral
oil
from
the
engine
and
fill
with
additive
oil.
2.
Do
not
operate
the
engine
longer
than
five
hours
before
the
first
oil
change.
3.
Check
all
oil
screens
for
evidence
of
sludge
or
plugging
and
change
oil
every
ten
hours
if
sludge
conditions
are
evident.
Resume
normal
oil
drain
periods
after
sludge
conditions
improve.
2-64.
LUBRICATION.
2-65.
LUBRICATION
INSTRUCTIONS.
Proper
lubrication
procedures
are
of
immeasurable
value
both
as
a
means
of
prolonging
the
service
life
of
the
airplane
and
as
a
means
of
reducing
the
frequency
of
extensive
and
expensive
repairs.
The
periodic
application
of
recommended
lubricants
to
their
relevant
bearing
surfaces,
as
detailed
in
the
following
paragraphs,
together
with
the
observance
of
cleanliness,
will
insure
the
maximum
efficiency
and
utmost
service
of
all
moving
parts.
Lubrication
instruction
regarding
the
locations,
time
intervals,
and
type
of
lubricants
used
may
be
found
in
the
Lubrication
Chart.
To
insure
the
best
possible
results
from
the
application
of
lubricants,
the
following
precaustions
should
be
observed:
Issued:
1/3/78
HANDLING
AND
SERVICING
1C13
60
62
Table of Contents
Table of Contents
3
Schematic Diagram of RSA Fuel Injection System
7
Electrical Symbols
11
Landing Gear
13
Scope of Manual
13
Brake System
14
Flight Controls
14
Fuel System
14
Instrument and Autopilot System
14
Section II Handling and Servicing
15
Handling and Servicing
15
Dimensions
17
Serial Number Plate
17
Ia17
17
Station Reference Lines
17
Tools and Test Equipment
25
Torque Requirements
25
Installation of Flexible Hose Assemblies
31
Ground Handling
45
General
45
Leveling
46
Mooring
47
Parking
48
Taxiing
49
External Power Receptacle
49
Fuel System
50
1C2
50
Filling Fuel Tanks
50
Draining Fuel System
51
Servicing
50
General
50
Brake System
51
Servicing Brake System
51
Filling Brake Cylinder Reservoir
51
Draining Brake System
51
Hydraulic System
54
Servicing Hydraulic System
54
1C6
54
Servicing Hydraulic Pump Reservoir
54
Landing Gear System
54
Servicing Landing Gear
54
Inspection
77
Sectionv Surfacecontrols
131
Wing
131
Surface Controls
132
Description
132
Introduction
132
Control Column Assembly
138
Removal of Control Column Assembly
138
Aileron Controls
139
Removal of Aileron Control Cables
139
Installation of Aileron Control Cables
140
Removal of Aileron Bellcrank Assembly
142
Installation of Aileron Bellcrank Assembly
143
Rigging and Adjustment of Aileron Controls
143
Stabilator Controls
147
Removal of Stabilator Control Cables
147
Installation of Stabilator Control Cables
148
Rigging and Adjustment of Stabilator Controls
149
Stabilator Trim Controls
153
Removal of Stabilator Trim Assembly (Forward)
153
Installation of Stabilator Trim Assembly
154
Removal of Stabilator Trim Controls (Aft)
155
Installation of Stabilator Trim Controls (Aft)
155
Rigging and Adjustment of Stabilator Trim
155
Rudder and Steering Pedal Assembly
156
Installation of Rudder and Steering Pedal Assembly
157
Rudder Controls
159
Removal of Rudder Control Cables
159
Installation of Rudder Control Cables
160
Rigging and Adjustment of Rudder Controls
162
Rudder Trim Controls
162
Removal of Rudder Trim Controls
162
Sectionvi Hydraulic System
181
Description
181
Hydraulic System
181
Assembly of Hydraulic Pump
192
Installation of Hydraulic Pump
193
Gear Back-Up Extender Actuator Assembly
193
Removal of Gear Back-Up Extender Actuator Assembly
193
Installation of Gear Back-Up Extender Actuator Assembly
194
Check and Adjustment of Gear Back-Up Extender Actuator
196
Nose Gear Actuating Cylinder
199
Removal of Nose Gear Actuating Cylinder
199
Disassembly of Nose Gear Actuating Cylinder
200
Cleaning, Inspection and Repair of Nose Gear Actuating Cylinder
201
Assembly of Nose Gear Actuating Cylinder
201
Installation of Nose Gear Actuating Cylinder
201
Main Gear Actuating Cylinder
201
Removal of Main Gear Actuating Cylinder
201
Disassembly of Main Gear Actuating Cylinder
203
Cleaning, Inspection and Repair of Main Gear Actuating Cylinder 1111
203
Assembly of Main Gear Actuating Cylinder
203
Installation of Main Gear Actuating Cylinder
204
Hydraulic Lines
204
Sectionvii Landing Gear and Brake System
219
Description
221
Introduction
221
Landing Gear System
225
Nose Landing Gear System
225
Disassembly of Nose Gear Oleo
225
Cleaning, Inspection and Repair of Nose Gear Oleo
226
Assembly of Nose Gear Oleo
226
Removal of Nose Landing Gear
228
Cleaning, Inspection and Repair of Nose Landing Gear
230
Installation of Nose Landing Gear
230
Adjustment of Nose Landing Gear
236
Alignment of Nose Landing Gear
237
Removal of Nose Gear Door Assembly
238
Cleaning, Inspection and Repair of Nose Gear Door Assembly
239
Installation of Nose Gear Door Assembly
240
Adjustment of Nose Gear Doors
240
Main Landing Gear System
240
Disassembly of Main Gear Oleo
240
Cleaning, Inspection and Repair of Main Gear Oleo
245
Assembly of Main Gearoleo
245
Removal of Main Landing Gear
249
Cleaning, Inspection and Repair of Main Landing Gear
250
Installation of Main Landing Gear
251
Adjustment of Main Landing Gear
252
Alignment of Main Landing Gear
253
Cleaning, Inspection and Repair of Main Gear Door Assembly
256
Installation of Main Gear Door Assembly
256
Troubleshooting
225
Landing Gear Limit Switches
256
Adjustment of Nose Gear up Limit Switch
257
Adjustment of Main Gear down Limit Switch
258
Adjustment of Landing Gear Safety Switch (Squat Switch)
259
Adjustment of Gear Back-Up Extender Actuator Switch
259
Wheel Brake Assembly
269
Brake Master Cylinder (Hand/Parking Brake)
272
Brake Cylinder (10-27) (Toe Brake)
275
Brake Cylinder (1700) (Toe Brake)
275
Brake Cylinder (10-30) (Toe Brake)
278
Fuel System
291
2D12
291
Painted Tooth Centered in Timing Window
292
Timing Mark on Rotor Aligned with Pointer
292
Timing Light Connected to Magneto and Breakers
292
Checking Flyweight to Stop Pin Clearance
292
Checking Impulse Coupling for Magnetization
292
Orientation of Springs in Coupling Body
292
Checking Harness Lead Continuity
292
Checking Harness Lead Insulation Resistance
292
Removing Spring from Lead Assembly
292
Electrical System Troubleshooting
295
Temperature Pressure Chart
295
Aluminum Tubing Torque
295
Compressor Oil Charge
295
Oxygen System Component Limits
295
Propeller Installation
299
Propeller Blade Minor Repair
300
Propeller Governor
303
Engine Installation
306
Adjustment of Engine Controls
308
Fuel Injector
311
Fuel-Air Bleed Nozzle
313
Height of Spring in Distributor Block Tower
314
Contact Points
315
Engine Timing Marks
315
Timing Light Connected to Magneto
317
Timing Marks on Magneto Rotor
318
Cam End View of Magneto
322
Removing Impulse Coupling
323
Stop Pin Installation Dimension
324
Checking Flyweight Axial Wear with Drill Shank
325
Checking Flyweight Radial Wear with Gauge
325
Points of Coupling Body Wear
326
Acceptable and Deformed Coupling Springs
326
Lifting Inner End of Spring
328
Modified Pliers
330
Assembly Tool
331
Using Assembly Tool
331
Ferrule Positioned under Braid
331
Hydraulic System
291
Landing Gear and Brake System
291
1J3
291
Aerofiche Card no
291
Power Plant (Pa-32Rt-300) 2A8 Viiia
291
Power Plant (Pa-32Rt-300T) 2C8
291
Structure
291
Vsurface Controls
291
General/Engine
386
Engine
386
General
386
Airspeed Indicator
403
Troubleshooting
404
Troubleshooting
406
Manifold Pressure Gauge
407
Troubleshooting
407
Tachometer Indicator
407
Troubleshooting
408
Troubleshooting
409
Fuel Pressure Gauge (PA-32RT-300)
409
Troubleshooting
410
Turn and Bank Indicator
411
Troubleshooting
411
Electrical Instruments
412
Fuel Quantity Indicator
412
Troubleshooting
412
Oil Temperature Indicator
413
Electrical System
419
General
420
Index - Electrical System Schematics
422
Ammeter
443
General
455
Electrical System Component Loads
469
Electrical Symbols
487
Electrical Wire Coding
488
Electronics
501
Heating and Ventilating
512
Accessories and Utilities
520
4
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Piper Lance II Specifications
General
Manufacturer
Piper Aircraft
Max Takeoff Weight
3, 600 lb (1, 633 kg)
Crew
1
Horsepower
300 hp
Seats
6
Length
27 ft 7 in (8.41 m)
Capacity
5 passengers
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