Mooney M20M - Page 13

SERVICE AND MAINTENANCE
MANUAL
M20M MOONEY
AIRCRAFT
CORPORATION
5-00-00
GENERAL
5-00-03
WING FLAP SYSTEM
AIRCRAFT DESCRIPTION. The
M20M
series
of
Wing flaps
are
electrically
actuated
and
are
controlled
aircraft
are
four
place,
high-performance,
by
a
spring
loaded
"up-off-down"
switch
on
the
center
turbocharged,
single-engine,
low-wing
monoplanes.
console.
The
all-metal
airframe has
a
tubular-steel
cabin
frame
covered
with nonstructural
)00-04
ELECTRIC POWER
SYSTEM
aluminum
skins,
a
semi-monocoque
tailcone,
and
a
fuil-cantilever,
1.
The
Master
Switch
and
power
relay
control the
laminar-flow
wing.
Control
surfaces have structural
electrical
power
system,
comprised
of
two
belt driven
spar
construction
with stressed
skins
riveted
to
the
70
AMP,
28
Volt,
alternators
and
two
10
AMP
HR,
24
spars
and
ribs.
Dual
control
wheels
accompany
the
Volt,
batteries. The
altemator
systems
have
conventional
flight
controls. The
pilot’s
rudder
pedals
overvoltage protective relays
and
overvoltage
have
toe
brakes linked
to
individual
hydraulic
cylinders
annunciator
lights.
Circuit breakers
or
circuit
breaker
that
supply
pressure
to
the
hydraulic
disc brakes
on
switches
protect
the
electrical
wiring
and
equipment
each
main
gear
wheel.
Removable
cc-pilot
rudder
from
overloads.
pedals
are
standard
equipment.
The
tricycle landing
Standard
electrical
equipment
includes:
2-100
watt
gear,
having
a
steerable
nose
wheel
controlled
by
landing
lights,
2-100
watt
taxi
lights,
navigation
lights,
rudder
pedal
action,
is
fully
retractable.
The
wide-span
interior
lights,instrument
panel/glareshield
lights,
gear
trailing-edge
wing
flaps
are
electrically
operated.
For
and
stall
warning
system,
an
electrical
fuel boost
stabilizer
trim,
the
entire
empennage
pivots
vertically
pump,
an
electric
starter,
an
electric
gear
about
its
attaching
points,
retraction/extension
system,
with manual extension
5-00-01
LANDING
GEAR SYSTEM
override,
an
electric
trim
system
(optional)
and
an
electrical
flap
system.
The
electric
landing
gear
system
has
a
steerable
nose
INSTRUMENTS
wheel.
Single
disc
self-adjusting
hydraulic
brakes
are
5-00-05
featured
on
the
main
gear.
Gear
position
lights,
a
All
flight
instruments
are
in
the
shock-mounted
Night
warning
horn
and
a
gear
position
indicator
on
the
Panel.
Engine
instruments
are
in
the
co-pilot’s
panel.
floorboard
are
standard
equipment.
Bungee
springs
The
pitot
system
provides
air
pressure
to
operate
the
that
preload
the
the
retraction
mechanism
in
an
airspeed
indicator.
The
instrument
static
pressure
over-center
position
lock
the
gear
down.
An
air
system
has
two
static air
pickup
ports
tone
on
each
pressure
actuated
safety
switch
in
the
electrical
system
side
of
the
tailcone)
that
open
to
the
atmosphere.
An
prevents
electric
gear
retraction
on
takeoff until
a
safe
alternate
static
source
is
provided
on
center
console.
flying
speed
is attained.
A
gear
throttle
warning
horn
The
instrument
panel/glareshield
lighting
systems
have
sounds
when
the manifold
pressure
is
less than
a
manual
dimming
mechanisms.
pre-set
value
with
the
landing
gear
up.
The
electric
gear
retraction
system
has
a
manual
extension
system
5-00-06
CABIN
HEATING
VENTILATING
connected
to
the
gear
actuator
that
permits
manual
SYSTEMS
lowering
of
the
gear
in
the
event
of
an
electrical
The
heater muff
encasing
the
exhaust
system
is the
malfunction.
Lan~iing
gear
doors
fully
enclose
the
cabin
heat
source.
Hot
air
from
the
heater
muff,
mixed
wheel wells
to
reduce
sound
levels
and
increase
with
ambient
air,
controls
cabin
temperature.
Air
routed
performance.
from
the main heater
duct
system
to
noules
at
the
5-00-02
FLIGHT
CONTROL
SYSTEMS
windshield base
defrosts
the
windshield.
An
optional
defrost blower
motor
system
is available.
The
dual
flight
control
systems
can
be
operated
from
5-00-07
FUEL SYSTEM
either the
pilot
or
co-pilot
seat.
All
flight
controls
are
conventional
in
operation,
using pushpull
tubes
to
link
The
fuel
system
has
sealed,
integral
wing
tanks
in
the
the control surfaces
to
the control
wheels
and
rudder
forward,
inboard section
of each
wing.
Vents
at
the
aft,
pedals.
Formica
guide
blocks
maintain control tube
outboard
top
comer
of
each
tank
vent
through
a
NACA
alignment
and
dampen
vibration.
An
interconnect
scoop
on
the
lower
wing
surface.
Fuel
sump
drains
are
spring
mechanism links the
aileron and rudder
systems
at
the
lowest
point
in
each
tank.
The electric
fuel
pump
to
assist in control coordination.
The
standard
cc-pilot’s
is in
the
bottom
left
forward
section
of the
fuselage,
aft
rudder
pedals
are
removable.
A
dual
brake
installation
of the firewall. The
engine-driven
fuel
pump
mounts
on
is
optional
for
the
cc-pilot’s
position.
The
manual
or
the
engine
crankcase.
Two
fuel
quantity
transmitters
in
electric
trim
system
sets
the
horizontal stabilizer
angle
each
tank
are
wired in
series
to
fuel
quantity
gauges
in
of
attack.
the
engine
cluster
gauge.
The Master
Switch,
left
side
of
the
pilot’s
panel,
activates the
fuel
quantity
indicating
systems.
The
optional
visual
sight
gauges
are
for
partial
fueling
of
wing
tanks..
A
"low
fuel"
warning
annunciator
light
for each tank
is
activated
when usable fuel
quantity
goes
below
2
1/2
gallons.
4-99
5-00-00
OLDWILLWAYNE