Piper Lance II User Manual

LANCE
II
SERVICE
MANUAL
SECTION
V
SURFACE
CONTROLS
5-1.
INTRODUCTION.
This
section
explains
the
removal,
installation,
and
rigging
and
adjustment
procedures
for
the
control
assemblies
of
the
various
structural
surfaces.
For
the
removal
and
installation
of
the
structural
surfaces
of
the
airplane,
refer
to
Section
IV.
The
assemblies
need
not
be
removed
in
order
of
paragraph
since
each
paragraph
describes
the
individual
removal
and
installation
of
the
various
assemblies.
The
following
tips
may
be
helpful
in
the
removal
and
installation
of
the
various
assemblies:
a.
It
is
recommended,
though
not
always
necessary,
to
level
and
place
the
airplane
on
jacks
during
rigging
and
adjustment,
especially
when
using
a
bubble
protractor
or
level.
b.
Remove
the
turnbuckle
barrels
from
cable
ends
before
withdrawing
the
cable
through
the
structures.
c.
Tie
a
cord
to
the
cable
end
before
drawing
cable
through
structures
to
facilitate
reinstallation
of
cable.
d.
When
turnbuckles
have
been
set
to
correct
tension,
no
more
than
three
threads
should
be
exposed
from
either
end
of
the
turnbuckle
barrel.
Locking
clips,
after
installation,
should
be
checked
for
security
by
trying
to
remove
the
clips
using
only
the
fingers.
Both
locking
clips
may
be
inserted
in
the
same
hole
of
the
turnbuckle
barrel,
or
they
may
be
installed
in
opposite
holes.
Locking
clips
should
not
be
reused.
e.
When
push
rods
or
rod
ends
are
provided
with
an
inspection
hole,
the
screw
shall
be
screwed
in
sufficiently
far
to
pass
the
hole.
This
can
be
determined
visually
or
by
feel,
inserting
a
piece
of
wire
into
the
inspection
hole.
Where
no
inspection
hole
is
provided,
there
shall
be
a
minimum
of
3/8
inch
thread
engagement.
f.
When
installing
rod
end
jam
nuts,
refer
to
Figure
5-la
for
proper
installation
method.
g.
Turnbuckle
terminals
should
be
screwed
an
approximately
equal
distance
into
the
barrel.
During
adjustment,
the
terminals
should
not
be
turned
in
a
manner
which
would
put
a
permanent
twist
in
the
cable.
h.
After
completion
of
adjustment,
tighten
and
inspect
each
jam
nut
thoroughly.
5-2.
DESCRIPTION.
The
Lance
II
is
controlled
in
flight
by
the
use
of
three
primary
control
surfaces,
consisting
of
ailerons,
stabilator
and
rudder.
Operation
of
these
controls
is
through
the
movement
of
the
control
column-tee
bar
assembly
and
rudder
pedals.
On
the
forward
end
of
each
control
column
is
a
sprocket
assembly.
A
chain
is
wrapped
around
the
sprockets
to
connect
the
right
and
left
controls
and
then
back
to
idler
sprockets
on
the
column's
tee
bar,
which
in
turn
connect
to
the
aileron
primary
control
cables.
The
cables
operate
the
aileron
bellcrank
and
push-pull
rods.
The
stabilator
is
controlled
by
a
cable
connected
to
the
bottom
of
the
tee
bar
assembly
and
operates
an
aft
fuselage
bellcrank
which
controls
a
push
rod
connected
to
the
balance
arm
of
the
stabilator.
Cables
also
connect
the
rudder
pedals
with
the
rudder
sector.
Provisions
for
directional
and
longitudinal
trim
control
is
provided
by
an
adjustable
trim
mechanism
for
the
stabilator
and
rudder.
The
stabilator
trim
is
controlled
by
a
wheel
and
drum
mounted
on
the
floor
tunnel
between
the
front
seats.
Cables
routed
aft
from
the
drum
to
a
screw
assembly
mounted
above
the
stabilator
attachment
point.
This
screw
assembly
in
turn
moves
the
push
rod
which
controls
the
stabilator
trim
tab.
The
rudder
trim
is
controlled
by
a
knob
and
screw
assembly
attached
to
the
rudder
pedal
assembly.
Revised:
10/3/80
SURFACE
CONTROLS
1F12

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