Mooney M20K - Fuelsystem Circuits; Landing Gear Circuits; Lighting Circuits

SERVICE
AND
MAINTENANCE
MANUAL
M20K
MOONfi~
AIRCRAFT
CORPORATION
2435-00
-LIGHTING
CIRCUITS
remain
ON
for
appro>dmately
2
minutes.
The
rocker
Navigation
Lights.
A
circuit
breaker
switch
on
the
switch
is
connected
through
the
MASTER
switch
on
these
aircraft
and
inten~or
lights
will
gp
out
when
the
flight
panel
controls
the
navigation
lights.
The
GEAR
MASTER
switch
is
turned
OFF
if door Is
closed.
DOWN,
GREEN,
annunciator
light
is
dimmed
when
NAV
Light
switch
is
ON.
7.
Map
Light.
A
push
button
switch on
top
of
control
wheel
center
section
controls
map
light (S/N
25-0001
2.
Landing/Taxi
Lights.
A
circuit
breaker
switch
thru
25-1224.
S/N
25-1225
thru
25-1230
have a
(25-0001
thru
25-0009)
(split
switch
for
25-1000
thru
switch/rheostat on
control
wheel
to
control
light
3
25-~230)
on
flight
panel
controls the
landing/taxi
lights
brightness.
The
cPpilots map
light
is
optional.
in
the
lower
engine
nacelle
(25-0001
thru
25-1224),
in
each
wing
leading
edge
(25-1225
thru
25-1230).
24-36-00
LANDING
GEAR
CIRCUITS
3.
Cabin
Lights.
A
three-position
(Bright,
Off,
Dim)
1.
Limit
switches
and
relays
operate
the
landing
gear
rocker
switchadjacent
to
the
door,
in
headliner,
actuator
a
12
volt
DC
(250001
thru
25-0999)
(24
volt
controls
cabin
forward
inten’or
lights.
for
25-li)00
thru
25-TEA)
reversible
motor
assembly.
A
landing
gear
air
pressure
safety
switch,
actuated
by
CAUTION
pitot
air
pressure,
prevents
landing
gear
retraction
until
On
S/N
25-0001
thru
25-1224
this
light
switch
is
a
safe
flying
speed
is
attained.
The
landing
gear
connected
directly
to
the
battery.
The
switch
control
switch
operates
the
actuator
motor
through
the
MUST
BE
TURNED
OFF
to
keep
from
safety
switch
and
relays.
Wnen
the
landing
gear
discharging
the
battery.
control switch
is
up
and
a
safe
flying
speed
has
been
attained,
the
safety
switch
closes
to
activate
control
Aircraft
SIN
25-1225
thru 25-1999
may
have
a
door
relay,
starting
the actuator.
As
the
gear
reaches
the
up
switch
and
timer
mechanism
that
illuminate
forward
set
,,d
locked
position,
a
mechanical
stop opens
the
up
of
inten’or
lights
while
cabin
door is
open.
After
door
is
limit
switch
and
the
actuator
stops.
When
the
landing
closed,
if rocker
switch
is
left
ON,
forward
interior
lights
gear
control
switch
is
placed
in the
down
position,
the
will
remain
ON for
appro>a’mately
2
minutes,
gear
motor
down-relay
closes
and
the
actuator
starts.
The
rocker
switch
is
connected
through
the
MASTER
When
the
gear
reaches
the
down-and-locked
position
switch
on
these
aircraft
and
forward
inten’or
lights
will
the
mechanical
stop
opens
the
dawn
limit
switch’anci
no
OFF
when
MASTER
switch
Is
turned OFF
if door
b
actuator
stops.
The
gear-up
limit
switch
controls
the
closed,
landing
gear
un-safe
light.
The
red
light
comes
on
4.
Anti-Collision
Lights.
A
circuit
breaker
switch
when
gear
is in
transit.
The
green
light
comes
on
when
controls
the
white
anti-collision
strobe
lights.
the
gear
reaches
down-and-locked
position;
the
5.
Instrument
and
Radio
Lights.
Rheostats
control
gear-down
limit
switch
controls
the
green
gear-down
and
radio
lights.
The
flight panel
light.
rheostat
controls
the
compass
light.
2.
Gear
Safety
By-Pass
Switch.
The
gear
will
not
Lighting
loads
are
controlled
by
transistors
biased
with
retract
if
airspeed
above
the set
limit
has
not
been
manuallY
controlled
rheostats.
The
transistors
can
be
attained
when
gear
handle
is
placed
in
the
UP
position.
checked
by
the
following
methods:
A
waming
hom
will
sound
and
both
"GEAR
DOWN"
A.
Conned
ohmeter
between
the
emitter
and
the
and
GEAR
UNSFE"
lights
will
illuminate.
Push
and
hold
the
red
button
switch
beside
the
landing
gear
collector-
should
be infinite
ohms.
handle
until
the
gear
is
up
and
both
lights
go
out.
Pull
B.
Short
base
to
collector
should
be
a
direct
the
circuit
breaker
"GEAR
CONT" or
"GEAR
RELAY
short,
zero
ohms,
to
stop
warning
hem.
Reset
circuit
breaker
prior
to
e~xtending
gear.
NOTE
If
readings
are
incorrect
reverse
the
loads.
243~90
FUEL
SYSTEM
CIRCUTTS
CAUTION
The
fuel
system
has
an
electric,
auxiliary
fuel
pump.
Care must
be
exercised
to
prevent
shorting
The
fuel
quantity
indicating
system
is
comprised
of
two
light
wires
when
installing
or
replacing
transmitters
in
each
fuel
tank
and
two
fuel
quantity
instruments.
Shorted
wires
will
cause
blown
gauges
(L
3
R)
in the
instrument
panel.
fuses
or
burned
out
transistors
in
the
control
box.
1.
Fuel
Pump
Circuits.
A
single
auxiliary
fuel
pump
is
controlled
by
3
switches
for
different
functions:
6.
Baggage
Compartment
Lights.
A
three-position
A.
Engine
Pn’me
This
switch,
located
on
(Bright,
Off,
Dim)
rocker
switch
in
headliner
controls
instrument
panel
above
the
throttle
control,
when
the
aft
interior
lights.
depressed
and
held
"ON"
causes
fuel
to
be
vaporized
CAUTION
and
injected
directly
into
the
induction
manifold
and
On
S/N
25-0001
thru
25-1224
this
light
switch is
engine
cylinders
for
starting.
connected
directlyto
the
battery.
The
switch
B.
Low
Boost
This
switch
is
located on
instrument
MUST
BE
TURNED
OFF
to
keep
from
panel,
lower
left,
near
master
switch
and
is used
when
discharging
the
battery.
switching
fuel
tanks
and
certain
emergency
situations.
Aircraft
S/N
25-1225
thru
25-1230
may
have
a
door
switch
and
timer
mechanism
that
illum~nate
aft
set
of
inten’or
lights
while
baggage
door
is
open.
After
door
is
closed,
if
rocker
switch
is
left
ON,
aft
interior
lights
will
24-35-00
OLDWILLWAYNE