Mooney M20R - Elevator; Vertical Stabilizers

SERVICE
AND
MAINTENANCE
MANUAL
M20R
MOONEY
AIRCRAFT
CORPORATION
7
1 I
1
3
6
1--/
5
DETAIL
A
AaP
ATOR FIGURE
55-2
55-10-02
HORIZONTAL STABILIZER
55-20-02
ELEVATOR
INSTALLATION
INSTALLATION
Refer
to
Section
53-40-02
for installation.
CAUTION
Each
new,
repaired
or
repainted
elevator should
be
55-20-00
ELEVATOR
checked
for balance
per
Section
27-91-00.
Elevators
on
the M20R consist
of
left and
rightj
hand
The
elevators
are
installed
in
reverse
order of
assemblies
attached,
through
ball
bearing
fittin~s
(1),
removal. Nominal
torque
values
for AN3 bolts
are
to
rear
spar
of
horizontal stabilizer
(Figure 55-2).:
to
be
used
(see
Section
5-20-01
for
torque
table.)
The elevator
control horn
(2)
is connected
to
inpoard
55-30-00
VERTICAL STABILIZER
leading edge
of each
elevator
(R.H.
and
L.H.).I
Both
control
horns
are
then connected
to elevator
flighft
con-
The
main
spar
assembly
(1) ~Fig.
55-3)
Is formed
from
tros belscrank.
The full
length
trim
tab
(3)
may
riot
be
aluminum
sheet. Formed
angle
doublers
(2)
are
nested
re-adjusted
from
factory
installed
setting.
This is
fiectory
inside main
spar
channel
and riveted
to
spar
web.
Rear
set at
70
down. spar
(3)
is
an
extrusion used
to
attach aft end
of
sec-
The elevator skins
~4)
are
stretch-formed
for
uppgr
and
tioned ribs
(4).
Stub
spar
(5)
is
also formed from
sheet
lower
surface of
elevator. There
are no
ribs
in
el$vator
aluminum.
A
doubler channel
(6)
is
attached
to vertical
between inboard
and outboard ribs.
The skins
dre
at-
stabilizer
stub and stub
spar
of
horizontal
stabilizer.
tached
to
leading edge
extrusion
(5)
and ribs
(6b
with
This
attach
channel
is
securely
bolted
to
stinger
blind
rivets.
Each formed
corrogation
is
match$d
on
bulkhead
brackets.
The
main
spar
doublers
and
angles
top
and
bottom skins and rivets
are
installed
for
(7,
8
and
9)
provide
attach
points
for
stinger
and
strength
and
rigidity through
each
corrogation,
horizontal
stabilizer
spar.
(Figure
55-3).
A
lead balance
weight
(7)
is
installed
in
each
el~vator
Skins
(10)
are
stretch-formed
in
2
sections
and
riveted
tip
with
iron
rivets
or
bolts
(8). (Figure
55-2).
Sec)
Sec-
to
ribs
and
spar.
tion
27-96-00
for
balancing procedures
on
elevatoi~s.
The
rudder
attach
fittings
(11)
are
mountedto
rear
spar
55-20-01
ELEVATOR
REMOVAL
extrusion
to
attach
rudder
(12).
Lead
weights
(13)
are
added for
dampening.
Remove AN3
bolts from
each
control horn
and
’push-
pull
tube
bearing,
then
remove
AN3 bolts
and
hatajware
55-30-01
VERTICAL
STABILIZER
REMOVAL
from
each
hinge fitting
on
both
elevators.
The
vertical
and
horizontal
stabilizer
are
removed
as a
unit
with
stinger
assembly.
Remove
fairing
located
on
tailcone which
covers
gap
between
tailcone
and
em-
pennage.
Section
53-40-02
describes
attaching
points
for
complete
empennage
assembly.
Refer
to
this
sec-
tion
for
removal
of
empennage
assembly
from
airplane.
55-10-02
Island Enterprises