Mooney M20R - Aircraft Description; Fuel System; Landing Gear System; Time Limit Components

SERVICE AND
MAINTENANCE
MANUAL
M20R
MOONEY
AIRCRAFT
CORPORATION
5-00-00
-GENERAL
i. The
Master Switch
and
power
relay
control
the
AIRCRAFT
DESCRIPTION.
The M20R
series of
electrical
power
system,
comprised
of
a
100
AMP,
28
aircraft
are
four
place,
high-performance,
normally
Volt,
altemator
and
two
10
AMP
HR,
24
Volt,
batteries.
aspirated,
single-engine,
low-wing
monoplanes.
The
The alternator
system
has
an
overvoltage
protective
all-metal
airframe has
a
tubular-steel
cabin frame
relay
and
an
overvoltage
annunciator
light.
Circuit
covered with
nonstructural
aluminum
skins,
a
breakers
or
circuit
breaker
switches
protect
the
semi-monocoque
tailcone,
and
a
full-cantilever,
electrical
wiring
and
equipment
from
overloads.
laminar-flow
wing.
Control
surfaces
have
structural
Standard electrical
equipment
includes:.
2-100
watt
spar
construction
with
stressed
skins riveted
to
the
la"ding lights,
2-100
watt
taxi
lights,
nawgation lights,
spars
and ribs.
Dual
control
wheels
accompany
the
interior
lights,instrument
panel/glareshield
lights,
gear
conventional
flight
controls. The
pilot’s
rudder
pedals
and stall
warning
system,
an
electrical fuel
boost
have
toe
brakes linked
to
individual
hydraulic
cylinders
pumpl
an
electric
starter,
an
electric
gear
that
supply
pressure
to
the
hydraulic
disc
brakes
on
retraction/extension
system,
with
manual extension
each
main
gear
wheel.
Removable,
cc-pilot
rudder
override,
an
electric
trim
system
(optional)
and
an
pedals
are
standard
equipment.
The
tricycle
landing
electrical
flap
system.
gear,
having
a
steerable
nose
wheel
controlled
by
5-00-05
-INSTRUMENTS
rudder
pedal
action,
is
fully
retractable. The
wide-span
trailing-edge wing
flaps
are
electrically
operated.
For
All
flight
instruments
are
in the
shock-mounted
Flight
stabilizer
trim,
the entire
empennage
pivots
vertically
Panel.
Engine
instruments
are
in
the
co-pilot’s
panel.
about its
attaching
points.
The
pitot
system provides
air
pressure
to
operate
the
airspeed
indicator. The
instrument
static
pressure
5-00-01
LANDING GEAR
SYSTEM
system
has
two
static
air
pickup
ports
tone
on
each
The
electric
landing
gear
system
has
a
steerable
nose
side
of the
tailcone)
that
open
to
the
atmosphere.
An
wheel.
Single
disc
self-adjusting
hydraulic
brakes
are
alternate static
source
is
provided
on
center
console.
featured
on
the
main
gear.
Gear
position lights,
a
The
instrument
panel/g]areshield
lighting
systems
have
warning
horn and
a
gear
position
indicator
on
the
manualdimming
mechanisms.
floorboard
are
standard
equipment.
Bungee springs
that
preload
the the
retraction
mechanism in
an
5-00-06
CABIN
HEATING
VENTILATING
over-center
position
lock the
gear
down.
An air
SYSTEMS
pressure
actuated
safety
switch in the
electrical
system
The
heater muff
encasing
the
exhaust
system
is
the
prevents
electric
gear
retraction
on
takeoff until
a
safe
cabin
heat
source.
Hot air
from the
heater
muff,
mixed
flying
speed
is
attained.
A
gear
throttle
warning
horn
with
ambient
air,
controls cabin
temperature.
Air
routed
sounds
when the manifold
pressure
is less
than
a
from the main
heater duct
system
to
nozzles
at
the
pre-set
value
with
the
landing
gear
up.
The
electric
windshield
base
defrosts
the
windshield.
An
optional
gear
retraction
system
has
a
manual
extension
system
defrost
blower
motor
system
is
available.
connected
to
the
gear
actuator
that
permits
manual
lowering
of
the
gear
in
the
event
of
an
electrical 5-00-07 FU EL
SYSTEM
malfunction.
Landing
gear
doors
fully
enclose the
The fuel
system
has
sealed,
integral
wing
tanks in
the
wheel wells
to
reduce
sound levels and
increase
fonuard,
inboard section
of
each
wing.
Vents
at
the
aft,
performance.
outboard
top
corner
of
each tank
vent
through
a
NACA
5-00-02
FLIGHT
CONTROL
SYSTEMS
scoop
on
the lower
wing
surface. Fuel
sump
drains
are
at
the
lowest
point
in
each
tank. The
electn’e fuel
pump
The
dual
flight
control
systems
can
be
operated
from
is
in the bottom
left
forward
section
of the
fuselage,
aft
either
the
pilot
or
co-pilot
seat.
All
flight
controls
are
of
the
firewall.
The
engine-driven
fuel
pump
mounts
on
conventional
in
operation,
using
pushpull
tubes
to
link
the
engine
crankcase.
Two fuel
quantity
transmitters in
the
control
surfaces
to the
control wheels
and
rudder
each tank
are
wired
in
sen’es
to
fuel
quantity
gauges
in
pedals.
Formica
guide
blocks
maintain
control tube
the
engine
cluster
gauge.
The
Master
Switch,
left side
alignment
and
dampen
vibration.
An interconnect
of the
pilot’s
panel,
activates
the fuel
quantity indicating
spring
mechanism
links the
aileron
and
rudder
systems
systems.
The
optional
visual
sight
gauges
are
for
to
assist
in
control
coordination.
The
standard
co-pilot’s
partial fueling
of
wing
tanks..
rudder
pedals
are
removable. A dual
brake installation
is
optional
for
the
co-pilot’s
position.
The
manual
or
A 110w
fuel"
warning
annunciator
light
for each
tank
is
electric trim
system
sets
the
horizontal stabilizer
angle
activated
when usable
fuel
quantity
goes
below 2 1/2
of
attack.
gallons.
5-00-03
WING FLAP
SYSTEM
5-10-00
TIME
LIMIT
COMPONENTS
Wing flaps
are
electrically
actuated and
are
controlled
It
is
recommended that
overhaul
or
replacement
of
by
a
spring
loaded
"up-off-down"
switch
on
the
center
components
should be
accomplished
not
later than the
console.
specified period
of
operation
for that
component
or
in
accordance
with manufactures
service data
or
5-00-04
ELECTRIC
POWER
SYSTEM
airworthiness
directives.
REV. 10-98
5-00-00
Island Enterprises