Mooney M20K - Wing Flap System

IMOONEY
AIRCRAFT
CORPORATION
M20K
SERVICE
AND
MAINTENANCE
MANUAL
4.
Electric
Trim.
(4)
EDO AIRE
18
inch
Ibs.
AThe
clutch
torque
for
the electric
trim
system
(5)
S-TEC
-30
inch
Ibs.
should
be
checked
and
adjusted
(by
an
Avionics
Shop)
5.
Stabilher
Trim
Chain
Adjustment.
(Reference
for
the
following
settings
to
operate
the
autopilot
sys-
Figure
27-12).
tems
properly:
k
With
the
four
mounting
bolts
(1)
slack,
adjust
(1)
KFC
200
21
2 inch Ibs.
the
two
NAS428-3-4
bolts
(2)
to
obtain
maximum
ten-
(2)
KAP
100
21
2
inch
Ibs.
sion
on
chain
without
causing
binding.
(3)
KFC 150
21
+/-2
inch Ibs.
2740-01
Trim
System
Troubleshooting
BINDING
Check control
tubes
at
bulkhead
grommets
for rub
marks.
Check
Trim Actuator
threads for
galling/not
lubricated,
lube
per
Ch.
5.
ELECTRIC
CLUTCH
SLIPPING
Check
BINDING
symptoms
above.
Check
for
proper
clutch
settings.
Confirm full bus
voltage
is available
at
tn’m
motor.
NOTE
through
a
cable
link
system
(8)
connected to
the
jack
Maximum wear on
trim
tube,
where
it
passes
thru
shaft
actuator
horn
(9).
bulkhead
grommets,
is
.007
inch
per
wall
or.014
The
flap
switch
(10)
is self
centen’ng
from
the
down
inch diameter.
position
and located
on
the
console
adjacent
to
the
flap
position
indicator.
The
flaps
can
be
retmcted
com-
pletely by placing
the
switch
in the
up
position
or
to
WHEEL
any
setting
between
0
and
33
degrees
by
holding
in
up
ASSEMBLY
position
to
setting
desired and
then
centen’ng
to
stop
the
actuator.
Lubricate
the
actuator
gear
box
and
ball
screw
at
inter-
vals
with lubn’cants
prescribed
in
Chapter
5.
1.
Wing
Flap
Removal
and
Installation
k
Remove
wing
flap
hinge
fairing
to
expose
flap
push-pull
tube.
B.
Remove
bolt,
nut,
and
washer
from
Rapactuat-
attachment.
FLOORBOARD
STEPPED
O
‘3~yC2
2
STOP
NUT
81X ul
GEC\R
JAM
NUT-Y
U
U
\L
1
ASSEMBL
S27
FIGURE
27-12
STABILIZER
TRIM
CHAIN
ADJUSTMENT
0’
~-7
’f
27-50-00
WING
FLAP
SYSTEM
3
Push-pull
tubes and
bellcranks
interconnect
the
flaps.
actuator
(1)
connected
to
a
jack
shaft
(2).
The
jack
s
The
flaps
are
operated
by
an
electn’cal
motor
driven
shaft Is
connected
to actuator
bracket
(3)
(Figure
27-
13)
on
each
flap just
outboard
of
hinges
(4)
by
a
push-
pull
rod
end
bean’ng
(5)
and
hardware.
Each
flap pivots
about
four
hinges.
Travel
is
controlled
by
limit switches
(6)
and
(7)
and UP
stops
located at
outboard
hinges
I
P
(Flgure
27-13).
Flap
position
is indicated
in the
cockpit
LlGURE
27-13/FV\P
ACTUATOR
ASSY.
INSTAL
27-40-01
OLDWILLWAYNE