Piper Lance II User Manual

LANCE
II SERVICE
MANUAL
1-8.
HYDRAULIC
SYSTEM.
The
hydraulic
system
incorporates
an
electrically
driven
pump
which
is controlled
by a
selector
lever
on
the
instrument
panel
which
in
turn
operates
the
retraction
and
extension
of
the
landing
gear.
1-9.
BRAKE
SYSTEM.
The
brake
system
is
operated
hydraulically
and
controlled
by
a
hand
lever
connected
to
a
single
brake
cylinder
that
operates
both
wheel
brakes,
plus
individually
operated
toe
brakes.
1-10.
ENGINE.
Engine
models,
rated
horsepower
and
other
related
information
may
be
found
in
Table
II-I
of
Section
II.
1-11.
PROPELLER.
A constant
speed
propeller
is installed
and
controlled
by an
engine
mounted
governor
which
is
controlled
by
a
lever
on the
power
quadrant
in
the cockpit.
Propeller
specifications
may
be
found
in
Table
II-I
of
Section
II
and
Table
VIII
A-I
of
Section
VIII
and
VIIIA.
1-12.
FUEL
SYSTEM.
The
fuel
system
consists
of
two
interconnected
aluminum
tanks
in
the
leading
edge
of
the
wings,
a
strainer
bowl
with
fuel
screen,
fuel
selector
valve,
and
electrical
auxiliary
fuel
pump
and
an
engine
driven
fuel
pump.
1-13.
FLIGHT
CONTROLS.
The
flight
controls
are
conventional
equipment,
consisting
of
a control
wheel
which
operates
the
ailerons
and
stabilator
and
pedals
which
operate
the
rudder.
Duplicate
controls
are
provided
for
the copilot.
1-14.
CABIN
HEATER,
DEFROSTER,
AND
FRESH
AIR
SYSTEM.
Heated
air
for
the
cabin
and
defroster
is obtained
from
the
exhaust
system
shroud.
Fresh
air
is picked
up
from
an
inlet
in
the
leading
edge
of
each
wing
and
from
an inlet
in the
leading
edge
of fin.
The
air
is
routed
through
the
wings
to individually
controlled
outlets
located
just
forward
and
aft
of
the
front
seats.
The
fresh
air
from
the
fin
is routed
to
overhead
vents.
1-15.
RADIO.
Provisions
are
provided
for
the
installations
of
various
radio
equipment
along
with
microphone
and
headset
jacks,
loudspeaker
and
other
radio
navagation-equipment.
1-16.
INSTRUMENT
AND
AUTOPILOT
SYSTEM.
Provisions
for
instrument
installation
include
panels
for
engine
instruments
and
advanced
flight
instruments
as well
as
for
an
Autopilot
System.
Issued:
1/3/78
1A14
INTRODUCTION

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