Mooney M20R - Ovation Installation and user guide

O
SERVICE
END
IC~
~B
T1T
~f
]L
BTRC~AFT
CORPOR
ATION
LO
UIS
SCHREINER
FI E
LD,
E(E
RRVI
EEE,
TX
78028
ORIGINAL-
JUNE.,
1994
MANUAL
NUMBER
l60
REVISED
10-98
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
KERRVILLE,
TEXAS
VVARN
ING:
Manufactured
with
1,1,1
Trichloroethane
substances
which
are
determined to
harm
public
health
and
environment
by
destroying
ozone
in
the
upper
atmosphere.
This
warning
applies
to
placards
manufactured
at
Mooney
Aircraft
Corporation
facility
and
installed
on
the
Mooney
Aircraft
Model(s)
addressed
in
this
publication.
WARNING:
Manufactured
with
1,1,1
Trichloroethane
substances
which
are
determined to
harm
public
health
and
environment
by
destroying
ozone
in
the
upper
atmosphere.
This
warning
applies
to
certain
adhesives
procured
form
vendors
and
utilized
on
the
applicable
Mooney
Aircraft
Model(s)
addressed
in
this
publication.
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
LOG
OF
REVISIONS
Alwavs
destrov
supersededpages
when
you
Insert
revised
DATE
OF
SECTIONS
DATE
OF
SECTIONS
REVISION
AFFECTED
REVISION
AFFECTED
OCTOBER,
1998
TITLE
PAGE
LOG
OF
RR/ISIONS
INTRODUCTION
CHAPTER
5
CHAPTER
8
CHAPTER
21
CHAPTER
24
CHAPTER
27
CHAPTER
28
CHAPTER
30
CHAPTER
32
CHAPTER
33
CHAPTER
34
CHAPTER
37
CHAPTER
39
CHAPTER
51
CHAPTER
53
CHAPTER
57
CHAPTER
61
CHAPTER
71
CHAPTER
77
CHAPTER
79
CHAPTER
91
NCITE:
A
list
of
effective
pages
will
appear
at
the
beginning
of
each
chapter.
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
INTRODUCTION
CHAPTER
(System)
This
manual
provides
servicing
and
maintenance
infor-
The various
groups
contain
major
systems
information
mation
for
the
Mooney
Model
M20R,
Serial Numbers
such
as
flight
controls,
landing
gear,
etc.
The
systems
29-0001
and
ON.
Maintenance
actions
that
referto
a
lim-
are
arranged
numerically
per
GAMA
recommended
ited
number
of
aircraft
will
be
designated
by
serial
number
assignment,
It is
suggested,
for
example,that
number
of
applicable
airplanes.
"Fuel" be
identified
with the
Chapter
number
"28".
The
sequence
of
numbers,
28-00-00,
refers
to
the
General
The Part
Number’s
of
replacement
or
repair
parts
should
information
of
the
Fuel
Systems.
be
identified
using
the
Illustrated
Parts
Catalog
applica-
ble
to
Model
and
S/N of
aircraft
being
worked
on.
The
SECTION
(Sub-System)
correct
P/N
can
be
ordered
through
any
Mooney
Service
The
major systems
of
an
aircraft
are
broken
down
into
Center.
See
Section
91 for
exceptions
on
Electrical
Com-
sub-systems.
These
sub-systems
are
identified
by
the
ponents.
second
element
of the
sequence
of
numbers,
ie.,
28-20-00.
The
element
-20-
indicates
the
distribution
The
format
and
contents
of this
manual
are
prepared
in
portion
of the fuel
system.
accordance
with
GENERAL
AVIATION
MANUFACTUR-
ER’S
ASSOCIATION
(GAMA)
SUBJECT
(Unit)
Specification
No. 2.
The manual
is
supplemented
with
The
individual
units
within
a
sub-system
may
be
identi-
wiring
schematics
for
the
various model
year
air-
fled
by
a
third
element
of the
sequence
of
numbers,
planes,as
necessary.
These
are
located
in
envelopes
at
ie.,28-20-01.
This
number
is
assigned
by
the
manufac-
the
back
of the
manual
texts
pages,
turer
and
may
or
may
not
be
used
depending
upon
the
complexity
of
the maintenance
action
recommended.
APPLICATION
OF
NUMBERING
SYSTEM
NOTE
Revisions
or
reissues
of this
manual
are
not
Mooney
Aircraft
Corporation
is
in the
process
of
revising
automatically
provided
to
manual
holders.
Holders
all
applicable
maintenance
technical
publications
to
of
these
and
dther
Mooney
Technical
Publications
GAMA format.
When this
effort is
completed
any
publica-
should
complete
the
information on
the
"YELLOW
tion
concerning
maintenance
of
aircraft
will
conform
to
CARD"
located
at
the front
of
the
Title
Page
and
send
to
Mooney
Aircraft
Corporation,
P.O.
Box
72,
this basic
Any
person
wishing
infor-
Kerrville, TX.,
78029-0072,
Attn:
Service
Parts
mation
concerning
the
Fuel
Distribution
System
would
Department.
refer
to
the
pages
identified
as
,28-20-00,
in
any
mainte-
nance
oriented
publication.
These
pages
will be
num-
Notification
is
sent to
known
manual
holders
when
an-
bered
sequentially
within
each
system
breakdown
in the
other
manual
is
prepared
to
replace
the
subscription
and
current
Mooney
series
of
aircraft.
As
Mooney
aircraft
advises
that
no
more
revisions
will
be
sent
out.
The
new
models
become
more
complex
the
page
numbers
may
manual
will
require
a new
subscription
service. If
addi-
be
sequentially
numbered
within
sub-systems.
tional
Technical
Publications are
desired,
contact
the
The
table of
contents
in the
front of
each
Chapter
will
pro-
above
department
at
Mooney
Aircraft
Corporation
at
vide
a
list
of
systems
and/or
subjects
covered
in
the
(210)
896-6000,
ext.
271.
Chapter.
For
example:
Correspondence
conceming
maintenance or
part
num-
bers
on an
airplane
should
contain
the
aircraft
model
28-00
General
number
and
serial number.
The
serial
number
appears
28-10
Storage
on
the
identification
placard
located
on
the
aft
end,
left
(Tanks,
vents,
repair,
hand
side
of the
tailcone
below
the
hon’zontal
stabilizer.
etc.)
28-20
Distribution
(Boost
pumps,
fuel
lines,
ASSIGNMENT
OF
SUBJECT
MATERIAL
etc.)
The content
of
this
publication
is
organized
at
four
levels:
28-40
Indicating
(Sender
Units,
quantity
Group
gauges,
etc.)
Chapter
(System)
Section
(Sub-system)
Subject
(Unit)
If there
is
a
reason
to
distinguish
between
LEFT
HAND
or
RIGHT
HAND
fuel
quantity
sending
units
thenthe
number
would
be
expanded
to
28-40-01
(Left
Hand)
and
GROUP
28-40-02
(Right
Hand).
This
concept
will
apply
to
any
ex-
panded
information
throughout
the
publications.
These
are
primary
divisions
of the
manual
that enable
broad
separation
of
content,
ie.,
Airframe
systems
VS
Powerplant
systems.
These
groups
are
identified
by
tabs.
REV.
10-98
INTRODUCTION
Island Enterprises

SERVICE
AND
MAINTENANCE
MANUAL
MZOR
MOONEY
AIRCRAFT
CORPORATION
SUPPLEM~NTARY
PUBLICATIONS
The
following
list
of
Manufacturers
and/or
publicatio~ns
can
provide
servicing
and maintenance
information
on
com-
ponents
of the
Mooney,
Model
M20R
No
avionics
equipment
Manufacturers or
publications
are
listed
due
to
the
many
configurations
that
can
be
installed
in
the
airdraft.
These
can
be
obtained
from
the
repair
stations
for
a
par-
ticular
avionics
manufacturer.
Any
publications
available
from
Mooney
Aircraft
Corporation
are
listed
in the
Parts
Price
List
and
are
available
through
any
Mooney
Service
Center.
Most
manufa4turer/vendor
publications
are
not
availabel
through
Mooney
Air-
craft
Corporation,
these
should
be
obtained
from
the
applicable
ManufacturerNendor.
As
publications
on
various
components
become
available,
they
will
be
added
to
the list
below.
VENDOR
ADL~RESSES
PUBLICATIONS
ENGINE
PUBLICATIONS
The
following
maintenance
publications
can
be
obtgined
through
Teledyne
Continental
Motors,
Aircraft
Products,
P.O.
Box
90,
Mobile,
Alabama,
USA,
36601,
Attn:
Accounts
Receivable
(Prepaid
only).
Overhaul
Manual
for
Teledyne
Continental
Motors
Aircraft
10-550
Engine
Models,
Fom~
X30568A.
Illustrated
Parts
Catalog
for
Teledyne
Continental
Motors
10-550
series
aircraft
engines,
Form
X30569A.
Maintenance
Operators
Manual
for
Teledyne
Coritinental
Motors
10-550
aircraft
engines,
Form
X30565.
Service
Bulletins
Specify
model
of
engine
for
which
maintenance
data
is
desired
when
ordering.
Fuel
Injector
Manual,
Form
X30593A
ACCESSORY
PUBLICATIONS
PROPELLER
BAcCauley Propellers
Obtain
publications
from
McCauley
Accessories
Division,
3535
McCauley
Drive,
Vandalia,
OH.,45377.
Service
Manual
No.
761001
for
McCauley
C400
series
constant
speed
propellers.
MAGNETO
Teledyne
Continental
Motors,
Aircraft
Products,
P.b.
Box
90,
Mobile,
Alabama,
USA,
36601,
Attn:
Publications
Dept.,
for TCM
(Bendix),
Type
S6RN-25
Series
magnetos.
ALTERNATOR
Alternator
Service
Instructions,
Form
X30531-3,
Teledyne
Continental
Motors,
Aircraft
Products,
P.O.
Box
90,
Mo-
bile,
Alabama,
USA,
36601,
Attn:
Publications
Dept.
STARTER
Service
Manual,
Teledyne
Continental
Motors,
Aircraft
Products,
P.O.
Box
90,
Mobile,
Alabama,
USA,
36601,
Attn:
Publications
Dept
FUEL PUMP
(Engine
Driven)
Teledyne
Continental
Motors,
Aircraft
Products,
P.O.
Box
90,
Mobile,
Alabama,
USA,
36601,
Attn:
Publications
Dept
IGNITION
SYSTEM
Master
Service
Manual,
TCM
Ignition
Systems
and
Components,
Form
X40000,
Teledyne
Continental
Motors,
Air-
craft
Products,
P.O.
Box
90,
Mobile,
Alabama,
USA,
36601,
Attn:
Publications
Dept
I
Precise
Flight,
Inc.,
63120
Powell
Butte
Rd.,
Bend,
OR
97701,
Telephone:
(503)
382-8684
SPEED
BRAKES
INTRODUCTION
Rev.
8-95
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
CHAPTER-
SECTION-
TITLE
INDU(GUIDE
CHAPTER
SECTION
TITLE
1 4
RESERVED
MAY
BE
USED
LATER
5
TIME
LIMITS/MAINTENANCE
CHECKS
00
GENERAL
10
TIME
LIMITS
20
SCHEDULED
MAINTENANCE
CHECKS
6
DIMENSIONS
AND
AREAS
00
GENERAL
7
LIFTING
10
JACKING
8
LEVELING
AND
V~EIGHING
00
LEVELING
9
TOWING
AND
TAXIING
00
GROUND
HANDLING
10
TOV\nNG
20
TAXIING
30
EMERGENCY
PROCEDURES
10
PARKING
AND
MOORING
00
GENERAL
10
PARKING
20
MOORING
11
PLACARDS
AND
MARKINGS
00
GENERAL
10
MARKINGS
20/30
PLACARDS-
UC~ERIOWINTERIOR
12
SERVICING
00
SERVICING
10
REPLENISHING
20
SCHEDULED
SERVICING
20
STANDARD
PRACTICES
-AIRFRAME
00
GENERAL
21
ENVIRONMENTAL
SYSTEMS
00
CABIN
VENTILATION
SYSTEM
40
HEATING
50
COOLING
60
TEMPERATURE
CONTROL
24
ELECTRICAL
POWER
00
GENERAL
30
DC
GENERATION
40
EXTERNAL
POV~R
50
ELECTRICAL
LOAD
DISTRIBUTION
REV.8-95
INTRODUCTION
Island Enterprises

SERVICE
AND
MAINTENANCE
MANUAL
M20R
MOONEY
AIRCRAFT
CORPORATION
CHAPTER
SECTION
TITLE
25
EQUIPMENT/FURNISHING
THIS
SECTION
MAY
NOT
BE
INCLUDED
1N
THIS
S 8 M.
00
GENERAL
10
FLIGHT
COMPARTMENT
20
PASSENGER
COMPARTMENT
50
CARGO
COMPARTMENT
60
EMERGENCY
EQUIPMENT
70
ACCESSORY
COMPARTMENT
27
FLIGHT
CONTROLS
00
GENERAL
10
AILERON
SYSTEM
20
RUDDER
SYSTEM
30
ELEVATOR
SYSTEM
40
STABILIZER
TRIM
SYSTEM
50
WING FLAP SYSTEM
60
INTERCONNECT
90
MISCELLANEOUS
28
FUEL
00
GENERAL
10
STORAGE
20
DISTRIBUTION
30
DUMP
40
INDICATING
90
MISCELLANEOUS
30
ICE AND RAIN
PROTECTION
00
GENERAL
10
AIRFOIL
30
PITOT AND
STATIC
40
WINDSHIELDS
60
PROPELLERS
32
LANDING GEAR
00
GENERAL
10
MAIN
LANDING GEAR
AND
DOORS
20
NOSE
LANDING GEAR
AND DOORS
30
EXTENSION
AND
RETRACTION
40
WHEELS
AND
BRAKES
50
STEERING
60
POSITION
AND WARNING
80
MISCELLANEOUS
33
LIGHTS
00
GENERAL
10/20
INTERIOR
LIGHTS
MAINTENANCE
PRACTICES
40
EXTERIOR LIGHTS
MAINTENANCE
PRACTICES
34
NAVIGATION
00
GENERAL
10
PITOT
8
STATIC
AIR
PRESSURE
SYSTEM
20
DIRECTIONAL GYRO
COMPASS
INTRODUCTION
REV.
10-98
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE MANUAL
CHAPTER
SECTION
TITLE
39
ELECTRICAL
PANELS
AND
COMPONENTS
00
GENERAL
10
INSTRUMENT
AND
CONTROL
PANELS
20
ELECTRICAL
AND
ELECTRONICS
EQUIPMENT
RACKS
51
STRUCTURES
00
GENERAL
10
STRUCTURAL
REPAIR
GENERAL
52
DOORS
00
GENERAL
10
CABIN
DOOR
MAINTENANCE
PRACTICE
30
BAGGAGE COMPARTMENT
DOOR
MAINTENANCE
PRACTICE
53
FUSELAGE
00
GENERAL
10
MAIN
FRAME
’20
AUXILIARY
STRUCTURE
30
PLATES/SKIN
40
ATTACH
FITTINGS
50
FILLETS/FAIRINGS
55
STABILIZERS
00
GENERAL
10
HORIZONTAL
STABILIZER
20
ELEVATOR
30
VERTICAL STABILIZER
40
RUDDER
56
WINDOWS
00
GENERAL
20
WINDSHIELD CABIN
WINDOWS
50
PLEXIGLASS
DRILLING
57
WINGS
00
GENERAL
30
PLATES/SKINS
40
ATTACH
FITTINGS
50
FLIGHT
SURFACES
60
STANDARD
PRACTICES
PROPELLERS
61
PROPELLERS
00
GENERAL
10
PROPELLER
ASSEMBLY
20
CONTROLLING
71
POWERPLANT
00
GENERAL
10
COWLING
INTRQDUCTIQN
Island Enterprises

SERVICE
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M20R
MOONEY AIRCRAFT
CORPORATION
CHAPTER
SECTION
TITLE
72
ENGINE
-RECIPROCATING
00
GENERAL
73
ENGINE
FUEL SYSTEM
00
GENERAL
10
DISTRIBUTION
20
CONTROLLING
30
INDICATING
74
IGNITION
00
GENERAL
10
POWER
CONTROL
20
EMERGENCY
SHUTDOWN
76
ENGINE
CONTROLS
00
GENERAL
10
POWER
CONTROLS
RIGGING
77
ENGINE
INDICATING
00
GENERAL
10
POWER
20
TEMPERATURE
EXHAUST
00
GENERAL
10
INSTALLATION
30
EXHAUST
SYSTEM
40
REPLACEMENT
COMPONENTS
79
OIL
00
GENERAL
10
STORAGE
20
DISTRIBUTION
30
INDICATING
80
STARTING
00
GENERAL
10
CRANKING
oo
TURBINES/EXHAUSTGENERAL
91
SCHEMATICS
00
GENERAL
20
ELECTRICAL
SYSTEM
HARDWARE
CHARTS
30
SCHEMATICS
95
SPECIAL
EQUIPMENT
INTRODUCTION
Rev.
4-95
Island Enterprises

CHAPTER
TIME
LIMITS/
MAINTENANCE
CH
EC
KS
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
CHAPTER
5
TIME
LIMITS/MAINTENANCE
CHECKS
TABLE
OF
CONTENTS
CHAPTER
SECTION
SUBJECT
SUBJECT
PAGE
5-00-00
General
5
5-00-01.
Landing
Gear
System
5
5-00-02.
Flight
Control
Systems
5
5-00-03.
W~ng
FlapSystems
5
5-00-04.
Electric
Power
System
5
5-00-05.
Instruments
5
5-00-06.
Cabin
Heating
3
Ventilating
Systems
5
5-00-07.
Fuel
System
5
5-10-00.
Time
Limit
Components
5
5-10-01
Overhaul
and
Replacement
Schedule
6
5-20-00.
Schedule
Maintenance
Checks
7
5-20-01
Check
Points,
Torque
Values
7
5-20-02
Aircraff
File
Inspection.
11
5-20-03
Engine
FunctionalCheck
11
5-20-04
First
25 Hour
Inspection
11
5-20-05
50
Hour
Inspection
11
5-20-06
100 Hour
Inspection
12
5-20-07
Access
Cover
Identification,
Lubrication
and
Service
Guide
15
REV.
10-98
5-CONTENTS
3/4BLANK
Island Enterprises

SERVICE
AND
MAINTENANCE
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M20R
MOONEY
AIRCRAFT
CORPORATION
CHAPTER
5
TIME
LIMITS/MAINTENANCE
CHECKS
LIST
OF
EFFECTIVE
PAGES
CHAPTER
SECTI
ON
SUBJECT.
PAGE
DATE
ti-Effectivity
1/2BLANK
10-98
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10-98
5-Contents
6-94
5-00-00
5.
5-10-00
6
10-98
5-20-01
7
10-98
5-20-01
8.
6-94
5-20-01
9.
6-94
5-20-01
10
10-98
5-20-02
?1
10-98
5-20-06
12
10-98
5-20-06
13
10-98
5-20-06
14
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5-20-06
15
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6-94
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5-20-07
17
5-20-07
18
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19
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5-20-07
20
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REV.
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5-EFFECTIVIN
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SERVICE AND
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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

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
The
specified
overhaul
time
limits,
if
applicable
tO
a
NOTE
component,
do
not
constitute
a
guarantee
that the
"ON
CONDITION"
items
are
to
be
repaired,
component
will
reach
that
time
limit
without
requi~ng
replaced
or
overhauled
when
inspection
or
maintenance.
performance
reveals
an
unserviceable
condition.
5-1
0-01
OVERHAUL,
MAINTENANCE AND
REPLACEMENT
SCHEDULE
ITEM
RECOMMENDED
OVERHAUL,
MAINTENANCE
OR
REPLACE
TIME
LIMITS
Landing
Gear
Actuator
No-Back
Spring
1000
Hours
Avionics
Prddcts(Eaton)
See
SI
M20-52A
Plessey-(GEC)
See
SI
M20-92A
I
All
other
Components
On
Condition
Powerplant
Engine
2000
Hours
Propeller
2000
Hours
or
6
years
(refer
to
mfg’s.
repair
data)
I
Magnetos
-iCEjl
500
Hours
(refer
to
TCM
repair/inspection
data)
induction
Air
Filter
500 Hours
or
Annually
(recommended)
All other
Components
On
Condition
Fuel
IL Oil
System
Fuel
Selector
Valve
(Airight
or
Christopher
Tool)
On
Condition
Flexible
Hoses
(All,
except
TeRon
5
as
below).
7
years
or
Engine
O/H,
whichever
occurs
first.
All
other
Components
(in~cludes
Teflon
hoses)
On
Condition
Instruments
Vacuum
Regulator
Garter
Filter
100
Hours
Filters-
Vacuum
Pump
500
Hours
(CV1J4
Filter-
On
Condition)
Filters
Gyro
Instruments
500
Hours
or
Annually
I
Other
Components
On
Condition
Electrical
System
All
Components
Oni
Condition
Flight
Controls
All
Components
On;
Condition
Miscellaneous
Systems
Vacuum
Pump,
Primary.
On
Condition
or
500 Hrs.
6
gB
Engine
O/H
I
Stand-by
Vacuum
Pump/Clutch
200
Hours
(Insped
Drive
Coupling)
E.L.T.
Battery
2 Years
or
1
Hour
Total
Use
Oxygen
Cylinders
I
*Lt. VI1t.
Steel
Cylinders
5
y;rs.(O/H)/
24
yeaw
or
10,000
recharge
cycles
Replace
Composite
C_ylinders
3
y;rs.(O/H)/
i
5
years
or
10,000
recharge
cycles
Replace
Scott
Oxygen
Regulator
6
years-overhaul;
3
years-test
Air
Conditioning Components.
SeeSedion
ii
-5800 for
specific
maintenance
and
seNicing
times.
All Other
Components
(Excluding
Avionics)
On Condition
(See
NOTE
above)
Avionics
Referto Manufacturers
Publications
Hydrostatic
Test
Required
3
yepr
intervals.
NOTE
Components
should
be
inspected
and
serviced
at
regular
intervals
per
the
servicing,
lubrication
and
inspection
chart of
this
manual.
5-1 0-00
REV.
10-98
Island Enterprises

SERVICE
AND
MAINTENANCE
MANUAL
M20R
MOONEY
AIRCRAFT
CORPORATION
5-2060
-SCHEDULED
MAINTENANCE
4.
Pipe
Threads
Tightening
and
torque
procedures.
CHECKS
Lubricate
pipe
threads
as
follows:
Inspection
Intervals.
Perform
a
25, 50,
or
100-hour
Oxygen
Lines
Use
only
MlL-T-5542
thread
inspection
of
the
aircraft,
components
and
engine
at
compound
or
Teflon thread
seal
tape
on
threads
of
valves,
connectors,
fittings,
parts
or
assemblies
which
recommended
intervals as
outlined
in
the
following
with
oxygen.
The
thread
might
come
in contact
paragraphs,
compound
must
be
applied
sparingly
to
the
first three
NOTE
threads
of the male
fitting only.
No
compound
is
to
be
Aircraft
operated
in
a
salt
air environment
are
used
on
the
coupling
sleeves
or on
the
outside
of
the
considered
high
risk
for corrosion
damage,
and tube flares.
Extreme care
should
be
exercised
to
should
be
cleaned
and
inspected
at
frequent prevent
the
contamination
of
the
thread
compound
or
intervals.
Refer
to
AC
43-4.
teflon
tape
with
oil,
grease
or
other
lubricant.
Fuel,
Hydraulic,
Air,
Oil
Lines Use
"Parker
Thread
5-20-01
-INSPECTION
CHECK POINTS
Lube"
or
equivalent
on
male
fittings only.
Apply
The
general
points
to
be
covered
during
inspection
are
lubricant,
omitting
the first
two
threads,
sparingly
and
grouped
in
accordance
with
the
nature
and function
of
carefully.
the items
discussed.
Engine
Fittings
Use
only
aircraft
engine
oil
to
Moving
Parts
shall be
inspected
and checked
as
lubricate
fittings
threaded
directly
to
engine.
Vacuum Lines
No
lubn’cation
is
to
be used.
Check
applicable
for:
proper
operation,
security
of
attachment,
manufacturers
instructions
when
installing
sealing,
cleanliness,
lubrication,
servicing,
safetying,
components.
Refer
to
Section
37 for maintenance
adjustment,
tension,
travel,
condition
of
hinges,
procedures
on
vacuum
system.
binding,
excessive
wear,
cracking,
corrosion,
Tapered
Threads
Use
Teflon
Threadseal
Tape.
deformation,
and
any
other
apparent
damage.
2.
Metal Parts
shall
be
inspected,
as
applicable,
for:
(1)
Continue
to
tighten
until
fitting
is
correctly
security
of
attachment,
condition
of
finish
and/or
p0sitioned
but do
not
overrun or
backoff.
sealant,
distortion,
fatigue
cracks,
welding
cracks,
(2)
If leaks
are
detected,
tighten
one
full
tum
more.
corrosion,
and
any
other
apparent
damage.
The
(3)
If
leaks
persist,
the
parts
should
be
tubular
frame structure
should
be
inspeded
during
disconnected
and
rejected;
replace
with
new
each
annual
inspection
for
any
signs
of
corrosion
or
components.
damage.
5.
Bolts and
nuts
in
critical
areas
shall
be
inspected
3.
Fuel, air,
oil and
hydraulic
oil lines
and
hoses
shall
for:
fretting,
wear,
damage,
stretch,
proper
torque,
be
inspected
as
applicable
foc
cracks,
dents, kinks,
(Figure
5-2)
and
safetying.
deterioration,
obstruction,
chaffing,
improper
bend
radius,
and
insecure
installation.
Replace
or
correct
if
6.
Electrical
wiring
shall be
inspected
as
applicable
any
of these
conditions
exist.
Hose
clamp
fO’:
loose,
corroded,
and broken
terminals;
chaffed,
installations
on
fuel
and
hydraulic
systems
between
broken,
and
wom
insulation;
insecure
installation;
heat
systems
or
between
systems
and the
engine
shall be
deterioration;
and
any
other
apparent
damage.
torqued
to
25
inch
pounds.
Hose
clamp
7.
Filters
and
screens
shall be
removed,
cleaned
and
installations
on
blast
tubes,
air
ducts,
vacuum
inspected
for
contamination
or
damage
that would
lines,
drain
and
vent
lines
shall be
torqued
to
15
require
replacement.
inch
pounds.
TORQUE
VALUES
See
Following
Tables.
REV. 10-98
5-20-00
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
MZOR
SERVICE
AND
MAINTENANCE
MANUAL
FLARE
NUT
TORQUE
VALUES-
T~ghten
to
min’imum
torque
value for
appropriate
size
as
shown
(Figure
51).
CAUTION
These
torque
values
are
deri)/ed
from
oil-free
cadmium-plated
threads.
FITTING
SIZE
ALUMINUM
TUBING
STEEL
TUBING
TORQUE
INCH
POUNDS
MINIMUM
i
MAXIMUM
MINIMUM
MAXIMUM
-3
30
70
-4
4b
,j
50
90
-5
60
80
70
120
-6
75
125
90
150
-8
150
250
155
250
-10
200
i
350
300
400
-12
300
500
430
575
-16
500
700
550
750
-20
600
900
-24
600
1
900
FLAPENUTMWUE
FIGURE 51
METRIC
BPLTS.
SCREWS
8 NUTS
Failure
of
threaded
fasteners
due
to
over-tightening
can
occur
by
bolt
shank
fracture
or
by
stripping
of
the
nut
and/or
bolts
thread.
A bolt
or
screw
assembled
with
a
nut
of the
appropriate
class
is
intended
to
provide
an
assem-
bly
capable
of
being
tightened
to
the bolt
proof
load
without thread
stripping
occurring.
The
torque
value
to
be set
for
a
particular
size
of
54rew
is
dependent
upon:
1)
Material of
the
screw.
2)
Parent
material
(steel,
non-ferrous
metal
or
plastic).
3)
V~hether
the
screw
is untreated
or
plated.
4)
V~hether
the
screw
is
dry
or
lubricated.
5)
The
depth
of
the
thread.
TIGHTENING
TORQUES
Untreated
Hardware
(Black
Finish)
Fiicfion
Coefficienf
0.
14
NOMINAL
5.6
8.8
PROPERPI
10.9
12.9
DIAMETER
CLASS
(Coarre
Thread)
Nmlff.lb.
Nmlff~lb.
TORQUE Ma
Nmlff.lb.
Nmlff.lb.
Ms
0.60/0.44
1.37/11.01
1.92/1.42
2.30/1.70
M4
1.37/1.01
3.1
0121.29
4.40/3.25 5.25/3.87
Ms
2.70/1 .99
6.15/4.54
8.65/6.38
19.4n.6
Ms
4.6/3.3
10.5/7.7
15/11
18/13
M7
7.6/5.6
17.5/112.9
25/18.4
29/21.3
Ms
1118.1
2~1B
36/26
43/31
M10
22/16
51
137
72/53 87/64
M12
39/28
89/65
125/92
150/110
M14
62/45
i 41
1~103
198/146
240/in
Mis
95/70
21
5/1158
305/224
365/269
Mis
130/95
295/217
420/309
500/368
Mn
250/1 84
570/
800/590
960/708
M20
184/135
590/435
71 0/523
M24
31
5/232
1020/752
1220/899
M27
470/346
1070/789
1510/1113
1810/1334
M30
635/468
1450/1/069
2050/1511
2450/i
806
M33
865/637
19701i452
27/0/2042
3330/2455
M36
11111819
2530/11865
3560/2625
4280/31 56
M39
1440/1062
3290/a426
4620/5407
5550/4093
5-20-01
Island Enterprises

SERVICE
AND
MAINTENANCE
MANUAL
M20R
MOONEY
AIRCRAFT
CORPORATION
(METRIC
TORQUE
TABILES
CONTINUED)
8.8
~PSBIY
10.9
12.9
Nm/ft.lb.
Nm/ft.lb.
Nm/ft.lb.
TORQUE
Ma
MFn08xXlhS
38/28
45/33
73/53
88/64
M12
x
1.25
95/70
135/99
160/118
M14
x
1.5
150/110
210/154
M16
x
1.5
225/165
315/232
M18
x
1.5
325/239
460/339
550/405
M20
x
1.5
460/339
640/472
115
)316~dfja3;bl1
M24
x
2
TIGHTENING
TORQUES
Electrically
Zinc
Plated
Hardware
Friction
Coefficient
8.
125
10.9
62.9
Nm/ft.lb.
Nmm.lb.
Nm/ft.ib.
Nmm.lb.
5.6
8.8
0.56/0.41
1.28/0.94
1.80/1.33
2.15/1.59
2.90/2.14
4.10/3.02
4
Ic,rJ
5.75/4.24
8.10/5.97
Me
4.3/3.1
9.9/7.3
14/10.3
16.5/12.1
7.2!1!1/5.25
66.5/12.1
2~ij16.9
10.5/7.7
2~7
M12
36126
83/61
117/86.2
140/103
1
185/a36
220/1
62
M14
58/42
147
M20
1
390/287
550/405
660/486
M22
230/169
530/390
745/549
890/656
M30
590/435
1900/1401
2280/1681
RA33
8001590
2580/1902
3090/2278
s.e
fO.D
62.9
Plm/ft.lb.
Nm~t.lb.
Nm/ft.lb.
TORQUE
Rna
Ma
x
1
25/18
35/25
42/30
x
1.25
140/103
x1.25
M14x1.25
235/173
M16
x
1.5
210/154
295/217
350/258
1.8
570/420
BIA241x
2
720/531
METRIC
CONVERSION
FACTOR:
One
Nm(Newton
Meter~
.7375
Foot
Pound;
One
Foot
Pound
1.355818
Nna
5-2069
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
AN/MS STANDARD
BOLT,
NUTS
TORQUE
TABLES
FINE-fHREAD
SERIES
TENSION-type SMEAR-type
TENS1ON-type
SMEAR
-type
NUT/BOLT
AN()BOLTS
AN()BOLTS
NAS()
BOLTS
NAS()
BOLTS
SIZE AN365/AN310 AN364/AN320
AN365/AN310
AN364/AN320
NUTS
NUTS
NUTS
NUTS
8-36
12-15
7-9
10-32
20-25
12-15
25-30
15-20
1/4-28.
50-70
30-40
80-1
00
50-60
5/16-24
100-140
60-85
120-145
70-90
3/8-24
160-190 95-110
200-250
120-150
7/16-20
450-500
270-300
520-630
300-400
1/2-20
480-690
290-410
770-950
450-550
9/16-18
800-1 000
480-600
1100-1300
650-800
5/8-18
1100-1300
600-780
1250-1550
750-950
3/4-16
2300-2500
1300-1500
2650-3200
1600-1900
7/8-14
2500-3000
1500-1800.
3550-4350
2100-2600
1-14
3700-5500
2200-3300.
4500-5500
2700-3300
11/8-12.
5000-7000
8000-4200
6000-7300
3600-4400
11/4-12
9000-11000
5400-6600
11000-13000
6600-8000
COARSE-THREAD
SERIES
8-32
12-15 7-9
10-24
20-25 12-15
1/4-20.
40-50 25-30
5/1
6-18 80-90 48-55
3/8-16
160-185 95-1 00
7/16-14 235-255
140-155
1/2-13
400-480
240-290
9/16-12 500-700
300-420
518-11 700-900
420-540
314-10
1150-1600
700-959
7/8-9 2200-3000
1300-1800
TOFPQUE
VALUES
(Units
are
In$h-pounds) Figure
5-2
Reference: Federal Aviation
Agency
Advisory
Circular No.
43.13-1A,
p.
118
Recommended
Torque
Values for
Nut-Bolt
combination
(Units
are
inch-pounds)
1. Be
sure
nut
and/or bolt threads
are
clean
and
dry(unless Mfg,
states
otherwise).
2. Run
bolt
down
near
contact
with
washer
or
bearing
surface and check "friction
drag
torque" required
to turn
bolt/nut.
3. Add
"friction
drag torque"
to
the
recommended
torque
value from
Figure
5-2.
This
value is
considered "Final
Torque
Value".
(FRICTION
DRAG
TORQUE
i
REC’MD
TORQUE
FINAL
TORQUE).
CAUTION
DO
NOT
REUSE LOCKNUTS
IF THEY CAN BE RUN UP FINGER TIGHT.
5-20-01
REV.
10-98
10
Island Enterprises

SERVICE
AND
MAINTENANCE
MANUAL
M20R
MOONP/
AIRCRAFT
CORPORATION
8-20-02
-AIRCRAFT
FILE
INSPECTION
inspection
doors,
panels,
or
fairings.
After
the first
25
Aircraft
100-hour
and
annual
inspections
cover,
in
hours
of
operating
time,
a
new,
re-manufactured,
or
addition
to
examining
the
aircraft
proper,
a
review
of
newly
overhauled
engine
should
be
given
a
50-hour
the
status
of
compliance
with
current
Federal
Aviation
including
replacement
of the
lubricating
oil
Regulations.
This
review
includes
inspection
of the
Airplane
Flight
Manual,
Aircraft
Log
Book,
Engine
Log
1.
Engine
Inspections.
(Refer
to
engine
Book,
Propeller
Log
Book,
Registration
Certificate,
manufacturer’s
service
data
for
oil
change
frequency)
Airworthiness
Certificate,
Weight
5
Balance
Record,
A.
Drain
engine
oil
sump.
Engine
Service
Information,
Aircraft
Radio
Station
B.
Remove
and
clean
suction
oil
strainer;
reinstall
License
(if
applicable),
FAA
Airworthiness
Directives,
strainer
and
plug.
Safety
wire
strainer
plug.
and
Mooney
service
documents.
C.
Remove
and
replace
the
full-flow
oil filter
cartridge.
5-201)3
ENGINE
FUNCTIONAL
CHECK
D.
Remove
and clean
fuel
injector
fuel
strainer.
Prior
to
a
scheduled
100-hour or
annual
inspedion,
E.
Service
engine
oil
sump
with
proper
type,
grade,
and/or
25
hours
after
installation
of
new
or
overhauled
a"d
amount
of
lubricating
oil.
engine,
wash
down
the
engine
and
engine
components.
F.
Inspect
engine
intake
and
exhaust
systems
for
Then
perform
an
engine
runup
in
accord
with
procedure
evidence
of
leakage,
looseness or
damage.
recommended
in
the
Airplane
Flight
Manual.
Make
a
G.
inspect
spark plug
elbows
and
shielding
nuts
for
record
of
all
malfunctions
and
abnormalities.
After
the
security.
engine
runup,
comdete
a
differential
(hot
engine)
H.
Inspect
cylinders
for
evidence
of
ovemeating.
compression
check.
to
verify
conedion
of
malfunctions
Engine
Installation
inspections.
and
abnormalities,
perform
a
second
engine runup
and
a
I.
inspect
baffles
for
secure
anchorage,
close
fit
Right
test
after
completing
the
inspection.
around
cylinders,
and Freedom
from
cracks.
J.
Inspect
engine
controls
for
full
travel,
freedom
of
530-04
FIRST
25-HOURS
INSPECTION
movement,
and
security.
(Non-Repetitive)
K.
Drain
and
clean
fuel
strainer
(Gascolator)
I
The,
one
time,
25-hour
inspection
consists
of
a
visual
L.
Visually
inspect
fuel
and
oil
lines
for
security
of
inspedion
of
the
propeller,
engine,
and
aircraft
general
connections
and
evidence
of
leakage
or
damage.
condition,
including
a
preflight
inspection
as
outlined
in
M.
Wsually
inspect
induction
air
system;
check
the
Airplane
Flight
Manual.
The
inspection
does
not
opention
of
alternate-air
door
(refer
to
paragraph
require
removal
of
all
access
panels
or
disassembly
of
71-62-00).
components;
however,1
should
include
completion
of
N.
Inspect
engine
mount
bolts
firewall
5
Lord
all
lubrication
8
service
requirements.
The
inspection
isolator
mounts
for
security
and
condition.
should
be
extensive
enough
to
detect
any
damage
or
2.
Propeller.
maladjustment
which
might
jeopardize
Right
safety.
A.
Inspect
propeller
hub
and
spinner
for
general
After
the
Zrst
25
hours
of
a new
or
ovemauled
engine
condition,
looseness,
and/or
oil
leakage.
operation,
refer
to
paragraph
5-20-05
for
the
B.
Inspect
blades
for
nicks
and
cmcks.
Repair
any
recommended
engine
inspection.
discrepancy
prior
to ne~d
Right
1.
Visually
inspect
propeller,
spinner,
and
engine
3.
Cabin.
cowling;
remove
cowling.
A.
Inspect
brake
and
parking
brake
control
2.
Inspect
and
clean
induction
air
filter
a
aircraff
has
systems
for
proper
operation
and
fluid
level.
been
operating
under
dusty
conditions.
Check
B.
inspect
trim
system
and
indicator
for
free
operation
of alternate
air
door.
operation
and
travel.
3.
inspect
engine
compartment
for
evidence
of
fuel,
C.
Inspect
cabin
and
baggage
doors
for
damage,
proper
operation,
and
sealing.
oil
or
exhaust
leaks.
D.
Lights
Inspect
cabin
interior,
instrument
panel,
4.
Inspect
security
and
condition
of
equipment
position,antLcollision
and
landing
and
taxi
installed
on
engine.
5.
Insped
fuselage,
wing
and
empennage
for
"E:
Inspect
fuel
selector
valve, gascolator,
and
extemal
evidence
of
damage.
Pay
particular
attention boost
pump
for
proper
operation.
to
scratches
and
dents.
F.
Inspect
oxygen
system,
plumbing
and
6.
Inspect
windshields
and
windows
for
crazing,
attachments
(ifinstalled).
cracks,
and
scratches.
7.
Inspect
control
systems
for
binding,
excessive
4.
Landing
Gear.
freeplay,
and
damage.
tires
for
cuts,
blisters,
wear
and
proper
8.
Inspect
pitot
and
static
systems
for
possible
B.
Inspect
shock
discs
for
proper
e>dension
at
obstructions.
aircraft
static
weight.
9.
Inspect
aircraft
e>derior
for
security
of
bolts,
C.
inspect
hydraulic
brake
system
for
disc
or
pad
screws,
etc.
wear,
disc
warpage,
hydraulic
fluid
level
and
proper
10.
Inspect
and
service
batteries.
installation.
5.
~Hngs.
5-20QI
80+10UR
INSPECTIOPI
-(Repetitive)
A.
inspect
surfaces
and
tips
for
damage.
The
S0-hour
inspection
includes
all
requirements
of
the
B.
Inspect
ailerons,
aileron
attachments,
and
25-hour
inspection,
plus
the
necessary
removal
of
bellcranks
for
damage
and
proper
operation.
REV.
10-98
5-20-02
Island Enterprises

MOONEY
AIRCRAFT
CORPORATION
M20R
SERVICE
AND
MAINTENANCE
MANUAL
C.
Inspect
flaps
and
attachments
for
damage
~nd
exhaust/manifold
connections
and
engine
exhaust
proper
operation.
Cycle
flaps,
observe
travel
and
~ny
manifolds
(SEE
Pare.
5-20-06,
Q,
R
S
below).
evidence
of
binding.
H. Remove
and
clean
induction
air filter
(replace
at
D.
Lubricate
contrds
per
Section
5´•20-07,
if
necess~iry.
500
Hrs). Inspect
altemate
air
door
and
magnet
for
6.
Fuselage
and
Empennage.
security
and
operation.
Inspect
all
air
ducting
and
A.
Inspect
stabilizer, elevators,
fin,
and
Ndde~
for
connections
in the
induction
air
system
for
leaks.
damage,
proper
operation
and
proper
attachment.
i.
check
magnetos
for
grounding
and
a. Lubricate
controls
per
section
~20´•07,
if
necessery.
Sy"ch""ization
(timing
to
engine);
inspect
magneto
C.
Check
Trim
System
for
proper
operation,
points
for
condition,
clearance,
and
intemai
timing.
Inspect
distributor
block for
erosion
and
cracks.
Inspect
7.
See
Section
5-20-07
for
any
repetitive
50
tiour
cam
follower
felt
for
proper
lubrication,
and
remove
inspections
and
component
service
guides,
excessive
oil from
breaker
compartment.
At
500 hours
inspect magneto
per
TCM/magneto
maintenance
5-20-06
100-HOUR INSPECTION
for
manual.
Repair
or
replace
components,
if
required.
ANNUAL
INSPECTIONS)
J.
Inspect
baffles
for
secure
anchorage,
cracks,
(Refer
to
Pig.
53)
holes,
deformation,
and for
dose frt
around
cylinders.
Inspect
cylinders
for
bumed
paint
and
cracked
and
The
100-hour
(or
annual) inspection
is
a
broken
fins.
Inspect
baffle
sealant.
searching
inspection
of
the
entire
aircraft,
starter,
altemator,
I
for the
inspedion
includes
the
thorough
of
K.
Insped
accessory
case,
AIC
e~cterior,
engine
and
engine
compartment,
vacuum
pumps
hoses,
firewall
and
fittings
for
security
of
all
fuselage,
wing,
and
empennage
inspection
and
damage.
cover
plates,
and
fairings
at
all
systems
attach,
L.
inspect
tubular
engine
mount
for
cracks,
and
bearing
locations
(including
wing
and
damage
and
corrosion;
inspect
all
bolts
and rubber
to
fuselage
mating
points).
Operating
isolation
mounts
for
security
and
condition.
M.
Inspect engine
and
pmpeller
co~ds
for free
replacements
(See
Section
5-10-01)
and
Directives,
Airworthinessess
biieclives
Notes
(AD’s),
attachment
testing
of
components
is
to
be
included
at
this i
operation,
full
travel,
proper
connection
(security)
of
cable
when
applicable.
Comply
with
applicable
AA
housing
swage
at
the
HEAD tube
and
security
of
applicable
Mooney
or
Vendor
mandatory
NOTE
Bulletins
and
Instructions.
Check for
conformance
to
FAA
Specification
2A3
for
Cablecraft
control
cables
are
lubricated
for the
life
of
the central
cable.
DO
NOT
REMOVE seals
Model
aircraft.
or
lubricate
control
cable.
Recommended
100-hour/annual
and
special
inspe~ion
requirements
are
outlined
in
the
following
paragraphs:
N.
Inspect
propeller
govemor
for
evidence
of
leakage
and
mounting
security.
anengine
runup
in
accord with
100
hour
71-00-50.
i.
ENGINE
INSPECTION.
Prior
to
the i
remove
engine cowling
and
propeller
spinner.
O.
Inspect
engine
for
proper
set-up.
(566
TCM
engine
and
engine compartment
down.
Then
Service
information
for
IO-550-G
engine
and Section
recommended
in
TCM
Engine
Maintenance
P.
Inspect
battery
cables,
electrical
wiring,
and
Operators
Manual. To
verify
corection
of malfun
ignition
harness
for
condition,
secure
anchorage,
loose
and
abnormalities,
perform
a
second
runup
and
terminals,
and
bumed
or
chaffed
insulation.
test
after the
100-hour/annual
inspedion
engine
set-~p.
Q.
Inspect
batteries,
battery
mount
areas,
and
vent
A.
Complete
a
differential
(hot
engine)
compres$ion
system
for
condition
and
corrosion.
Inspect
blast tube
check
(Ref.
TCM SE M84-15
or
current
rev.):
clean
~nd
for
obstrction.
Flush
battery
mount
areas
with soda
gap
or
~place spark
plugs,
if
necessary.
solution
to
neutralize
conosive
action,
if
necessary.
B.
Inspect
engine
for
evidence of
fuel
andi
oil
R.
Inspect
exhaust
system
for
cracks,
looseness
leakage.
Inspect
oil cooler.
Inspect
oil
and fuel
hoises
and
for evidence
of
leakage. Replace
or
repair
for
condition and
security,
damaged
area.
Replace
or
repair
muffler
if
any
internal
clean oil
suction
screens;
reinstall
and
safety.C.
Drain
engine
oil
sump;
remove,
damage
is found.
full-flow oil
filter
cartridge; replace
with
new
S.
Inspect
exhaust
stacks for
bumed
areas,
cracks,
distortion and looseness.
and
safety.
It is recommended
that
old
filter
be
opehed
T.
Inspect
airconditioning
compressor
installation,
up
to
check for
metal
particles
8
foreign
matter.
Check
belts,connections
(if
installed).
Reference
SECTION
crank
case
breather
lines for obstruction.
Safety
ivire
21-58-00.
oil filter installation.
U.
Inspect
studs, nuts,
bolts,
etc.
For
damage
and
D. Refill
engine
oil
sump
with
the
proper
t~pe,
propertorque.
grade,
and
quantity
of
lubricating
oil.
V.
Inspect
exhaust
couplings,
seals,
clamps
and
E.
Inspect
fuel
injedor,
fuel line
connedionsjfor
slipjoints
for
cracks,
deformation,
leaks
and
security.
security
and
condition and
fuel naules
(Ref
TCM
SE).
W.
Inspect
and
re-install
cowling.
F. Remove and
inspect gascolator
strainer,
rein~tall
strainer.
Inspect
fuel lines
arid
connections:
pres$ure
2´•
PROPELLER
INSPECTION.
check fuel
system
with mi>dure
control
at
IDLE
CUTOFF
A. Remove
spinner (if
not
already
removed).
and
BOOST PUMP ’ON".
B.
Inspect
security
of
propeller
installation.
G.
Inspect
all air
ducting
and
connections
in
c~bin
C.
Inspect
hub
studs/nuts/bolts
for
proper
torque
I
heating
air
systems
for leaks. Leak
check
all
(ref.
81-00-20,5,6),
security
and
damage.
5-20-06
:REV.
10-98
12
Island Enterprises