Mooney M20K - Aircraft Description; Landing Gear System

MOONEY
AIRCRAFT
CORPORATION
M20K
SERVICE
AND
~AINTENANCE
MANUAL
5-0090
-GENERAL
annunciator
light.
Circuit
breakers
or
circuit
breaker
AIRCRAFT
DESCRIPTION.
The
M20K
series
of
switches
protect
the
electrical
wiring
and
equipment
from
overloads.
Standard
electrical
equipment
aircraft
are
four
place
high-performance
turt~ocharged
includes:
2-100
uvatt
landing
lights,
navigation
lights,
single-engine
low-wing
monoplanes.
The
all-metal
airframe
has
a
tubular-steel
cabin
frame
covered
with
interior
lights,
gear
and
stall
warning
system,
an
electn’cal
fuel
boost
pump,
an
electric
starter,
an
nonstructural
aluminum
skins,
a
semi-monocoque
tailcone,
and
a
full-cantilever
laminar-fio~nr
wing.
Control
electric
gear
retraction
system
with
manual
extension
ovem’de
and
an
electn’cal
flap
system.
surfaces
have
structural
spar
construction
with
stressed
skins
n’veted
to
the
spars
and
ribs.
Dual
2. An
optional
standby
generator
(12V,
10
amp)
is
control
wheels
accompany
the
conventional
flight
available
to
operate
basic
essential
components
in
the
controls.
The
pilot’s
rudder
pedals
have
toe
brakes
event
of
main
a8temator
failure
on
S/N
25-0613
thru
linked
to
individual
hydraulic
cylinders
that
supply
250999
aircraft.
An
optional
second
70
ampere,
belt
pressure
to
the
hydraulic
disc
brakes
on
each
main
driven
alternator
will
be
available
on
S/N
25-1000
and
gear
wheel.
Removable
cc-pilot
rudder
pedals
are
ON
aircraft.
standard
equipment.
The
tn’cycle
landing
gear,
having
a
steerable
nose
wheel
controlled
by
rudder
pedal
5-00-05
-INSTRUMENTS
action,
is
fully
retractable.
The
wide-span
trailing-edge
All
flight
instruments
are
in the
shock-mounted
flight
wing flaps
are
electrically
operated.
For
stabilizer
tn’m,
panel.
Engine
instruments
are
in
the
cc-pilot’s
panel.
the
entire
empennage
pivots
vertically
about
its
The
pitot
system
provides
air
pressure
to
operate
the
attaching points,
airspeed
indicator.
The
instrument
static
pressure
5-00-01
LANDING
GEAR
SYSTEM
system
has
two
static
air
pickup
ports
tone
on
each
side
of the
tailcone)
that
open
to
the
atmosphere.
An
The
electric
landing
gear
system
has
a
steerable nose
alternate
static
source
is
provided
on
lower
flight
wheel.
Single
disc
self-adjusting
hydraulic
brakes
are
instrument
panel.
The
instrument
panel
lighting
system
featured
on
the
main
gear.
Gear
position
lights,
a
has
manual
dimming
mechanisms.
warning
hom
and
a
gear
position
indicator on
the
floorboard
are
standard
equipment.
Bungee
spn’ngs
5-00-06
CABIN
HEATING
5
VENTILATING
that
preload
the
the
retraction
mechanism
in
an
SYSTEMS
over-center
position
lock
the
gear
down.
An
air
The
heater
muff
encasing
the
exhaust
system
is
the
pressure
actuated
safety
switch in
the
eledn’cal
system
cabin heat
source.
Hot
air
from
the heater
muff
m’uted
prevents
electric
gear
retraction
on
takeoff
until
a
safe
with
ambient
air
controls
cabin
temperature.
Air
routed
flying
speed
is
attained.
A
gear
throttle
waming
hom
f,,
the
main
heater
duct
system
to
nonles
at
the
sounds
when
the
manifold
pressure
is
less
than
a
windshield
base
defrosts
the
windshield.
pre-set
value
with
the
landing
gear
up.
The
electn’c
gear
retraction
system
has
a
manual
e~dension
system
590-07
FUEL
SYSTEM
connected
to
the
gear
actuator
that
permits
manual
lowen’ng
of the
gear
in
the
event
of
an
electn’cal
The
fuel
system
has
sealed,
integral
wing
tanks
in
the
malfunction.
forward,
inboard
section
of
each
wing.
Vents
at
the
aff,
outboard
top
comer
of
each
tank
vent
through
the
5-00-02
FLIGHT
CONTROL
SYSTEMS
lower
wing
surface.
Fuel
sump
drains
are
at
the
lowest
The
dual
flight
control
systems
can
be
operated
from
point
in
each
tank.
The
electric
fuel
pump
is
in
the
either
the
pilot
or
cc-pilot
seat.
All
flight
controls are
bottom
left
forward
section
of the
fuselage
just
aft
of
conventional
in
operation,
using
pushpull
tubes
to
link
the
firewall.
The
engine-driven
fuel
pump
mounts
on
the
control
surfaces
to
the
control
wheels
and
rudder
the
engine
crankcase.
Two
fuel
quantity
transmitters
in
pedals.
Formica
guide
blocks
maintain
control
tube
each
tank
are
wired
to
fuel
quantity
gauges
in
the
alignment
and
dampen
vibration.
An
interconned
engine
cluster
gauge.
The
master
switch,
left
side
of
spring
mechanism
links
the
aileron and
rudder
systems
the
pilot’s
panel,
turns
on
the
fuel
quantity
indicating
to
assist in
control
coordination.
The
standard
co-pilot’s
systems.
Visual
sight
gauges
are
available
for
partial
rudder
pedals
are
removable.
The
tn~m
system
sets
the
fueling
of
wing
tanks
on
aircraft
250001
and
UP.
stabilizer
angle
of attack.
A low
fuel
waming
annunciator
light
for
each
tank
is
activated
when
usable
fuel
quantity
goes
below
2
1~2
5-00-03
-WING FLAP
SYSTEM
gallons.
Wing
flaps
are
electrically
actuated
and
are
controlled
by
a
spring
loaded
"up-off-down"
switch
on
the center
5-10-00
TIME
LIMIT
COMPONENTS
console.
It
is
recommended
that
overhaul
or
replacement
of
5-00-04
ELECTRIC
POWER
SYSTEM
components
should
be
a
accomplished
not
later
than
the
specified
period
of
operation
for that
component
or
i.
The master
switch
and
power
relay
control
the
i,,ccordance
with
manufactures
service
data
or
electrical
power
system,
comprised
of
a
70
amp
14
Mit
,i,,rthiness
directives.
altemator,
a
voltage regulator,
and
a
12
volt,
35
AMP
HR
battery
(S/N
25-0001
thru
25-0999).
Aircraft
S/N
The
specified
overhaul
time
limits,
if
applicable
to
a
25-1000
and
ON have
a
70
AMP,
28
volt
altemator
and
component,
do
not
constitute
a
guarantee
that
the
a
24
volt,
22
AMP
HR
battery).
The
altemator
system
component
will
reach
that
time
limit
without
requiring
has
an
ovenroltage
protective
relay
and
an
overvoltage
maintenance.
5-00-00
OLDWILLWAYNE