Mooney M20M Installation and user guide

O
O
SEI~VICE
AND
MAINTEN
ANCE
MANUAL
~I
OONEY
AIRCR
AFT CORPOR ATION
LOUIS SCHREINER
FIELD,
KERRVILLE,
TX
78028
ORIGINAL
ISSUE
APRIL 1999
MANUAL NUMBER
51
OLDWILLWAYNE

MOONEY AIRCRAFT
CORPORATION
KERRVILLE,
TEXAS
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
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.
OLDWILLWAYNE

MOONEY AIRCRAFT CORPORATION
M20M
SERVICE
AND
MAINTENANCE MANUAL
LOG
DF
REVISIONS
ALwavs destrov
suPerseded
Da9es
when
vou
Insert revised
DATE
OF
SECTIONS DATE
CIF SECTILINS
REVISION
AFFECTED
REVISION
AFFECTED
NOTE:
A
list
of effective
Daaes
wil~
appear
at
the
bea;nninn
of
each
chapter,
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20M
SERVICE AND
MAINTENANCE MANUAL
INTRODUCTION
GROUP
This manual
provides
servicina
and
maintenance
information for
the
Mooney
Mlodel
M20M,
Serial
These
are
primary
divisions
of the
manual
that
enable
Numbers
27-0001
and
ON.
Maintenance
actions that
broad
separation
of
content,
ie.,
Airframe
systems
VS
Powerplant
systems.
These
groups
are
identified
by
tabs.
refer
to
a
limited
number of
aircraft
will
be
designated
by
serial number
of
applicable airplanes.
The
Part
Numbers
of
replacement
or
repair
parts
should be
SYSTEM/CHAPTER
identified
using
the illustrated
Paris
Catalog
applicable
to model
S/N
of aircraft
being
worked
on.
The
current
The
various
groups
contain
major
systems
information
P/N
can
be
ordered
through
any
Mooney Marketing
such
as
Right
controls,
landing
gear,
etc.
The
systems
Center
(MMC).
See
SECTION 91
for
exceptions
on
are
arranged
numerically
per
GAMA
recommended
electrical
components.
number
assignment,
It
is
suggested,
for
example,that
"Fuel"
be
identified
with
the
SystemlChapter
number
The
format and
contents
of this manual
are
prepared
in
"28".
accordance
with
GENERAL AVIATION
MANUFACTURER’S
ASSOCIATION
(GAMA)
The
sequence
of
numbers,
28-00-00,
refers
to
the
Specification
No.
2.
The
manual is
supplemented
with
General
information
of the
Fuel
Systems.
wiring
schematics for
the various
model
year
SUB-SYSTEM/SECTION
airplanes,as
necessary.
These
are
located in
Th,
major
systems
of
an
aircraft
are
broken
down
into
envelopes
at
the back
of
the manual
texts
pages.
sub-systems.
These
sub-systems
are
identified
by
the
NOTE
second
element
of
the
sequence
of
numbers,
ie.,
Revisions
or
reissues
to
this
28-20-00.
The
element
-20-
indicates the
distribution
portion
of the
fuel
system.
manual number
are
not
UNIT/SUBJECT
automatically
provided
to
manual
holders.
Holders
of
The
individual
units
within
a
sub-system
may
be identified
by
a
third dement
of
the
sequence
of
numbers,
these and
other
Mooney
ie.,28-20-01.
This number
is
assigned by
the
manufacturer
Technical
Publications
should
and
may
or
may
not
be
used
depending
upon
the
complete
the informatjon
on
the
c0mple~y
of
the
maintenance
action recommended.
YECLOW
CARD
located
at the
APPLICATION OF
NUMBERING SYSTEM
front of
the
Title
Page
and
send
MOO"ey
Aircraft
Corporation
prepares
all
applicable
to
Mooney
Aircraft
Corp_oratSon,
technical
publications
to
GAMA
format.
All
publications
concerning
maintenance
of
aircraft
will
conform
to
this
Louis
Sctitelner
Field,
Kerrville,
basic
numbering
system.
Any
person
wishing
TX.,
78028,
Attn:
Service
Parts
information
concerning
the
Fuel
Distribution
System
Department.
would
refer
to
the
pages
identified
as
28-20-00
in
any
maintenance
publication.
These
pages
will
be
numbered
sequentially
within
each
system
breakdown
Notification
is
sent
to
known manual holders when
in
the
current
Mooney
series
of
aircraft.
As
Mooney
another manual
is
prepared
to
replace
the
subscription
aircraft models become
more
complex
the
page
and advises
that
no more
revisions
will
be
sent out,
numbers
may
be
sequentially
numbered
within
The
new
manual
will
require
a new
subscription
sub-systems.
service.
If
additional Technical Publications
are
desired,
contact
the
Service
Parts
Department
at
The table
of
contents
in the
front of each
Mooney
Aircraft
Corporation
at
(830)
896-6000
UCT.
System/Chapter
will
provide
a
list
of
sub-systems
2092.
covered
in
the
Chapter.
For
example:
28-00
General
Correspondence
concerning
maintenance
or
part
numbers
on an
airplane
should contain the aircraft
28-10
Storage
model number and serial number. The serial number
CTanks,
vents,
repair, etc.)
appears
on
the identification
placard
located
on
the aft
end,
left
hand
side
of the
tailcone below the horizontal
28-20
Distribution
stabilizer.
(Boost
pumps,
fuel
lines,
etc.)
28-40
Indicating
ASSIGNMENT
OF
SUBJECT
MATERIAL
(Sender
Units,
quantity
gauges,
The
content
of
this
publication
is
organized
at
four
etc.)
levels:
If
there
is
a reason
to
distinguish
between
LEFT
HAND
Group
or
RIGHT HAND
fuel
quantity sending
units
then the
and
28-40-02
(Right
Hand).
This
concept
will
apply
to
number
would
be
expanded
to
28-40-01
(Left
Hand)
UnitlSubject
any
expanded
information
throughout
the
publications.
4-99
INTRODUCTION
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL M20M MOONEY AIRCRAFT
CORPORATION
SUPPLEMENTARY PUBLICATIONS
The
following
list
of
Manufacturers
and/or
publications
can
provide
servicing
and
maintenance
information
on
components
of
the
Mooney-TLS,
Model M20M.
No avionics
equipment
Manufacturers
or
publications
are
listed due
to
the
many
configurations
that
can
be installed
in
the aircraft. These
can
be
obtained from
the
repair
stations
for
a
particular
avionics manufacturer.
Publications
available
from
Mooney
Aircraft
Corporation
are
listed in the Parts
Price
List
and
are
available
through
any
Mooney
Service Center.
As
publications
on
various
components
become
available,
they
will
beadded
to
the list
below.
VENDOR ADDRESSES
or
PUBLICATIONS
ENGINE
The
following
maintenance
publications
can
be
obtained
through TUCTRON-Lycoming
Division,
Wiliiamsport,
PA.,
17701.
Overhaul
Manual
for
TEXTRON-Lycoming
Aircraft
Engines
Direct Drive Models.
Illustrated
Parts
Catalog
for
TEXTRON-Lycoming
TIG-540
series
aircraft
engines.
Operators
Manual
for
TEXTRON-Lycoming
TIG-540 aircraft
engines.
Service
Bulletins
Specify
model
of
engine
for
which
maintenance data
is
desired.
PROPELLER
McCauley
Propellers
Obtain
publications
from
McCauley
Accessories
Division,
Cessna Aircraft
Company,
3535
McCauley
Drive,
Vandalia, OH.,45377.
Service
Manual
No.
761001
for
McCauley
C400
series
constant
speed
propellers.
MAGNETO
Slick
Electro,
530
Blackhawk
Park
Avenue,
Rockford, 1161101,
for
Slick
Model
6260
or
6261
magneto.
TURBORCHARGER
Rotomaster,
c/o
Garrett-Aftenarket
Division,
2511
South
Edison
Way,
Compton,
CA
90220-6035,
Attn: Don
Winters
ALTERNATOR
Prestolite Electronics
Division,
511
Hamilton
Street,
Toledo,
OH
43694
STARTER
B
C
Specialty
Products
Inc.,
123
East 4th
Street,
PO
Box
B,
newton
KS
67114-0894.
Telephone
(316)
283-8662.
FUEL
PUMP
(Engine
Driven)
Lear
Siegler,
Romec
Division,
241
South Abbe
Road,
Elyria,
OH
44035
FUEL
INJECTOR
Precision
Airmotive,
3220-100th
Street,
S.W.
#E, Everett,
WA
98204
SPEEDBRAKES
Precise
Flight,
Inc. 63120 Powell Butte
Rd.,
Bend,
OR
97701,Telephone:
(503)
382-8684.
DE-ICING/ANTI-ICING
(TKS)
Aerospace Systems
8
Technologies,
Inc.,
110
Riverfront
Road,
Suite
C.
Lawrence,
KS
66044,
\NTRODUCTION
4-99
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20M
SERVICE
AND
MAINTENANCE MANUAL
CHAPTER
SECTION
TITLE
INDEX
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
WEIGHING
00
LEVELING
9
TOWING
AND
TAXIING
00
GROUND
HANDLING
10
TOWING
20
TAXIING
10
PARKING
AND
MOORING
00
GENERAL
10
PARKING
20
MOORING
11
PLACARDS
AND MARKINGS
00
GENERAL
10
MARKINGS
20
PLACARDS-
EXTERIOR/INTERIOR
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
24
ELECTRICAL
POWER
00
GENERAL
30
DC
GENERATION
50
ELECTRICAL
LOAD
DISTRIBUTION
25
SEATS
00
GENERAL
THIS
SECTION
IS
NOT
10
FLIGHT
COMPARTMENT
INCLUDED
IN
THIS
g0
PASSENGER
COMPARTMENT
MANUAL.
50
CARGO
COMPARTMENT
60
EMERGENCY
EQUIPMENT
70
ACCESSORY
COMPARTMENT
4-99
INTRODUCTION
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20M
MOONEY
AIRCRAFT
CORPORATION
CHAPTER
SECTION
TITLE
27
FLIGHT
CONTROLS
00
GENERAL
10
AILERON
SYSTEM
20
RUDDER
SYSTEM
30
ELEVATOR
SYSTEM
40
STABILIZER
TRIM
SYSTEM
50
WING
FLAP
SYSTEM
90
MISCELLANEOUS
28
FUEL
00
GENERAL
10
STORAGE
20
DISTRIBUTION
30
DUMP
40
INDICATING
50
MISCELLANEOUS
30
ICE
AND RAIN
PROTECTION
00
GENERAL
10
AIRFOILS
30
PITOT AND
STATIC
60
PROPELLER
32
LANDING
GEAR
00
GENERAL
10
MAIN
LANDING GEAR
8
DOORS
20
NOSE
LANDING
GEAR 8
DOORS
30
EXTENSION AND
RETRACTION
40
WHEELS
8
BRAKES
50
STEERING
60
POSITION
AND
WARNING
80
MISCELLANEOUS
33
LIGHTS
00
GENERAL
20
INTERIOR
LIGHTS
MAINTENANCE
40
PRACTICES
INTERIOR
LIGHTS
MAINTENANCE
PRACTICES
34
NAVIGATION
00
GENERAL
10
PITOT
STATIC AIR
PRESSURE
SYSTEM
20
DIRECTIONAL
GYRO
COMPASS
35
OXYGEN
00
GENERAL
37
VACUUM
00
GENERAL
10
DISTRIBUTION
20
INDICATION
INTRODUCTION
4-99
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER
SECTION
TITLE
39
ELECTRICAL
PANELS
AND
COMPONENTS
00
GENERAL
10
INSTRUMENT
CONTROL
20
PANELS,
ELECTRICAL 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
4-99
INTRODUCTION
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20M
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
12
POWER
CONTROL
20
EMERGENCY
SHUTDOWN
76
ENGINE
CONTROLS
00
GENERAL
10
POWER
CONTROLS
RIGGING
77
ENGINE
INDICATING
00
GENERAL
10
POWER
20
TEMPERATURE
78
EXHAUST
00
GENERAL
10
NSTALLATION
30
EXHAUST
SYSTEM
40
REPLACEMENT
COMPONENTS
79
OIL
00
GENERAL
10
STORAGE
20
DISTRIBUTION
30
INDICATING
80
STARTING
00
GENERAL
10
CRANKING
81
TURBINES
00
GENERAL
10
POWER
RECOVERY
20
TURBOCHARGER
91
ELECTRICAL
00
GENERAL
20
ELECTRICAL
SYSTEM
HARDWARE
CHARTS
30
SCHEMATICS
95
[NOT
INCLUDED
SPECIAL
EQUIPMENT
IN
THIS
MANUAL]
INTRODUCTION
4-99
OLDWILLWAYNE

CHAPTER
TIME
LIMITS/
MAINTENANCE
CH EC
KS
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20M
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.
FlightControl
Systems
5
5-00-03.
Wing
Flap
Systems
5
5-00-04.
Electric
Power
System
5
5-00-05.
Instruments
5
5-00-06.
Cabin
Heating
g
Ve~ilating
Systems
5
5-00-07.
Fuel
System
5
5-10-00.
Time
Limit
Components
6
5-10-01
Overhaul
and
Replacement
Schedule
6
5-20-00.
Schedule
Maintenance
Checks
7
5-20-01
Check
Points,TorqueValues
7
5-20-02
Aircraft
File
Inspection.
11
5-20-03
Engine
Functional
Check
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
17
9-CONTENTS
3/48LANK
4-99
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20M
MOONEY
AIRCRAFT
CORPORATION
CHAPTER
5
TIME
LIMITS/MAINTENANCE
CHECKS
LIST
OF
EFFECTIVE
PAGES
CHAPTER
SECTION
SUBJECT
PAGE
DATE
5-Effectivity
1/2BLANK
4-99
5-Contents
3/4BLAN
K
4-99
5-00-00
5.
4-90
5-10-00
6.
4-99
5-20-00
7.
4-99
5-20-01
8.
4-99
5-20-01
9.
4-99
5-20-01.
10
4-99
5-20-02
11
4-99
5-20-06
12
4-99
5-20-06
13
4-99
5-20-06
14
4-99
5-20-06
15
4-99
5-20-06
16
4-99
5-20-07
17
4-99
5-20-07
18
4-99
5-20-07
19
4-99
5-20-07
20
4-99
5-EFFECTIVITY
4-99
1/2BLANK
OLDWILLWAYNE

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

MOONEY
AIRCRAFT
CORPORATION M20M
SERVICE
AND
MAINTENANCE
MANUAL
5-10-00
TIME
LIMIT COMPONENTS
The
specified
overhaul
time
limits,
if
applicable
to
a
component,
do
not
constitute
a
guarantee
that the
It
is
recommended
that overhaul
or
replacement
of
component
will reach
that
time
limit
without
requiring
components
should
be
accomplished
not
later
than
the
maintenance.
specified period
of
operation
for
that
component
or
in
accordance with
manufactures
service
data
or
NOTE
airworthiness
directives.
"ON
CONDITION"
items
are
to
be
repaired,
replaced
or
overhauled
when
inspection
or
performance
revea!s~an
unserviceable
condition.
5-10-01
OVERHAUL
AND
REPLACEMENT
SCHEDULE
ITEM
RECOMMENDED
OVERHAUL OR
REPLACE
TIME
LIMITS
Landing
Gear
Actuator
No-Back
Spring
1000
Hours
All
other
Components
On
Condition
Powerplant
Engine
2000
Hours
(Reference
Lycoming
SI
1009AJ)
Propeller
2000
Hours
or
6
years
(Refer
to
Mfg.’s
maintenance
data)
Magneto
:Slick
4
years
or
Engine
O/H
CTBO)(refer
to
Slick
Electro
repair/O/H
data)
induction
Ai;
Filter
500
Hours
Natural
Rubber
Engine
isolators
(siack)
10
years
V-Band
Couplings
Gaskets
At
Engine
O/H
or
On
Condition
All
other
Components
On
Condition
Fuel
Oil
System
Fuel Selector
Valve
(Airight
Christopher
Tool)
On
Condition
Flexible
Hoses
(All,
except
as
below)
7
years
or
Engine
O/H,
whichever
occurs
first.
Aeroquip
601
Fuel
Hoses
24
Months
All
other
Components
(includes
teflon
hoses)
On
Condition
Instruments
Vacuum
Regulator
Garter
Filter
100
Hours
Filters Vacuum
Pump
500
Hours
(CVIJ4
Filter
On
Condition)
Filters
Gym
Instruments
500
Hours
or
Annually
TIT
Probe
200
Hours
Other
Components
On
Condition
Electrical
System’
All
Components.
On
Condition
Flight
Controls
All
Cbmponents
On
Condition
Miscellaneous
systems
VacuumPump,
Primary
On
Condition
or
500
Hours
or
Engine
O/H
Stand-by
Vacuum
PumplClutch
200
Hours
(Inspect
Drive
Coupling)
E.L.T.
Battery
2
Years
or
1
Hour
Total Use
Oxygen
Cylinders
Lt.
Wt.
Steel
Cylinders
24
years
or
10,000
recharge
cycles
Composite
Cylinders
15
years
or
10,000
recharge
cycles
Scott
Oxygen
Regulator.
6
years-overhaul;
3
years-test
All
Other
Components
(Excluding
Avionicsi
On
Condition
(See
NOTE
above)
Avionics
Refer
to Manufacturers
Publications
Bendix/King Systems
Refer
to
Bendix/King
Service
Memo No.
292
X
Hydrostatic
Test
Required
3
year
intervals.
NOTE
Components
should be
inspected
and
serviced
at
regular
intervals
per
the
servicing,
lubrication
and
inspection
chart
of
this
manual.
5-10-00
4-99
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20M
MOONEY
AIRCRAFT
CORPORATION
5-20-00
SCHEDULED
MAINTENANCE
Oxygen
Lines
Use
only
MlL-T-5542
thread
CHECKS
compound
or
TeRon
thread
seal
tape
on
threads
of
Inspection
Intervals.
Perform
a
25,
50,
or
100-hour
valves,
connectors,
fittings,
parts
or
assemblies
which
inspection
of
the
aircraft,
components
and
engine
at
might
come
in contact
with
oxygen.
The
thread
recommended
intervals
as
outlined
in
the
following
comp0u"d
must
be
applied sparingly
to
the
first three
paragraphs.
threads
of
the
male
fitting only.
No
compound
is
to
be
used
on
the
coupling
sleeves
or
on
the
outside
of the
NOTE
tube flares.
Exireme
care
should
be
exercised
to
Aircraft
operated
in
a
salt air
environment
are
prevent
the
contamination
of the
thread
compound
or
considered
high
risk
for
corrosion
damage,
and
teflon
tape
with
oil,
grease
or
other
lubricant.
should be
cleaned
and
inspected
at
more
Fuel,
Hydraulic,
Air,
Oil Lines
Use
"Parker
Thread
frequent
intervals.
Refer
to
AC
43-4.
tube"
or
equivalent
on
male
mings
only.
Apply
5-20-01
INSPECTION
CHECK
POINTS
lubricant,
omitting
the
first
two
threads,
sparingly
and
carefully.
The
general
points
to
be
covered
during
inspection
are
grouped
in
accordance
with the
nature
and
function
of
Engine
Fittings
Use
only
aircraft
engine
oil
to
the
items
discussed.
lubricate
fittings
threaded
directly
to
engine.
Vacuum
Lines
No lubrication
is
to
be
used.
Check
1.
Moving
Parts
shall
be
inspected
and
checked
as
instructions
when
installing
applicable
for:
proper
operation,
security
of
attachment,
ma"ufacturers
sealing,
cleanliness,
lubrication,
servicing,
safetying,
components.
Refer
to
Section
37
for
maintenance
adjustment,
tension, travel,
condition
of
hinges,
p’ocedures
on
vacuum
system.
binding,
excessive
wear,
cracking,
corrosion,
Tapered
Threads
Use
TeRon
Threadseal
Tape.
deformation,
and
any
other
apparent
damage.
(1)
Continue
to
tighten
until
fitting
is
correctly
2.
Metal
Parts
shall
be
inspected
and
checked
as
positioned
but
do
not
overrun
or
backoff.
applicable
for:
security
of
attachment,
condition
of
(2)
If
leaks
are detected,
tighten
one
full
tum
finish
and/or
sealant,
distortion,
fatigue
cracks,
welding
more.
cracks, corrosion,
and
any
other
apparent
damage.
The tubular frame
structure
should
be
inspected during
(3)
If
leaks
persist,
the
parts
should
be
each annual
inspection
for
any
signs
of corrosion
or
disconnected
and
rejected;
replace
with
new
damage.
components.
3.
Fuel,
air,
oil and
hydraulic
oil
lines
and
hoses
shall
5´•
Electrical
wiring
shall
be
checked
as
applicable
be
inspected
as
applicable
for:
cracks,
dents,
kinks,
for:
loose,
corroded,
or
broken
terminals;
chaffed,
deterioration,
obstruction,
chaffing,
improper
bend
broken,
or
worn
insulation;
insecure
installation;
heat
radius,
and insecure
installation.
Replace
or
correct
if
deterioration;
and
any
other
apparent
damage.
any
of
these
conditions exist.
Hose
clamp
installations
6.
Bolts and
nuts
in
critical
areas
shall
be
checked
on
fuel
and
hydraulic
systems
between
systems
or
for:
fretting,
wear,
damage,
stretch,
proper
torque,
between
systems
and the
engine
shall
be
torqued
to
(Figure
5-3)
and
safetying.
25
inch
pounds.
Hose
clamp
installations
on
blast
7.
Filters and
screens
shall
be
removed,
cleaned
and
tubes,
air
ducts,
vacuum
lines,
drain
and
vent
lines
inspected
for
contamination
or
damage
that
would
shall be
torqued
to
15
inch
pounds.
require
replacement.
4.
Pipe
Threads
Tightening
and
torque
procedures.
Lubricate
pipe
threads
as
follows:
TORQUE
VALUES
SEE
FOLLOWING
TABLES
4-99
5-20-00
OLDWILLWAYNE

MOONEY
AIRCRAFT CORPORATION M20M
SERVICE
AND
MAINTENANCE
MANUAL
FLARE NUT
TORQUE
VALUES-
Tighten
to
minimum
torque
value
for
appropriate
size
as
shown
(Figure
5-1).
CAUTION
These
torque
values
are
derived from
oil-free
cadmium-plated
threads.
FITTING
SIZE
ALUMINUM
TUBING.
STEEL TUBING
MINIMUM MAXIMUM
MINIMUM
MAXIMUM
-3
30
70
-4
40
65
50
90
-5
60
80
70.
120
-6
75
125
90.
150
-8
150 250
155
250
-10
200
350
300
400
-12
300
500
430
575
-16
500
700
550
750
-20
600
900
-24
600
900
FLARE NUT
TORQUE
FIGURE
5-1
METRIC
BOLTS,
SCREWS NUTS TORQUE
VALUES
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
assembly
capable
of
being tightened
to
the
bolt
proof
load without
thread
stripping
occurring.
The
torque
value
to
be
set
for
a
particular
size of
screw
is
dependent
upon:
1)
Material
of
the
screw.
2)
Parent
material
(steel,
non-ferrous metal
or
plastic).
3)
Whether the
screw
is
untreated
or
plated.
4)
Whether
the
screw
is
dry
or
lubricated.
5)
The
depth
of the thread.
TIGHTENING TORQUES
Untreated
Screw(Black Finish)
Friction
Coefficient
0. 14
NOMINAL
5.6
8.8
PROPERTY 10.9
12.9
DIAMETER
CLASS
(Coarse Thread)
Nm/ft.lb.
Nmm.lb.
TORQUE
Ma
Nm/ft.lb.
Nmm.lb.
M3
0.60/0.44
1.37/1.01
1.92/1.42
2.30/1.70
M4
1.37/1.01
3.10/2.29
4.40/3.25
5.25/3.87
M5
2.70/1.99 6.15/4.54
8.65/6.38
10.417.6
Ms
4.6/3.3
10.5/7.7
15/11
18/13
M7
7.6/5.6
17.5/1
2.9
25/1
8.4
29/21.3
M8
26/19
36/26
43/31
M10
22/16 51/37
72/53
87/64
M12
39/28
89/65 125/92
150/110
M14
62/45
141/103
198/146
240/177
M16
95/79
215/158
305/224
365/269
M18
130/95
295/217
420/309
500/368
M20
184/1
35
420/309
590/435
71
0/523
M22
250/1
84
570/420
800/590
96onos
M24
31
5/232
725/534
1020/752
1220/899
M27
470/346
1070/789
1510/1113
1
810/1334
M30
635/468 1450/1
069
2050/1
511
2450/1
806
M33
865/637 1970/1
452
2770/2042
3330/2455
M36
1111/819 2530/1
865
3560/2625
4280/31
56
M39
1440/1062 3290/2426 4620/3407
5550/4093
5-20-01
4-99
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20M
MOONEY AIRCRAFT
CORPORATION
(METRIC
TORQUE
TABLES
CONTINUED)
8.8
10.9
12.9
(Fine Thread)
NmP.\b.
~BPUE
Ma
Nmlft.\b.
Nmtft.\b.
M8x1
27/19
38/28 45/33
M10x1.25
52/38
73/53 88/64
M12x1.25
95/70
135/99
160/118
M14x1.5
150/110
21
0/1
54
250/1
84
M16x1.5
2251165
3151232
3801280
M18x1.5
325/239
460/339
550/405
M20
x1.5
460/339
640/472
770/567
M22
x
1.5
610/449
860/634
1050/774
M24
x2
780/575
1100/811 1300/958
TIGHTENING
TORQUES
E\ectrically
Zinc P\ated Friction
Coefficient
0.
125
DIAMETER
5.6
8.8
10.9
129
(Coarse
Thread)
Nmm.lb.
Nm/ft.lb.
TORQUE
Ma
Nmlft.lb. Nmlft.lb.
M3
0.56/0.41
1.2810.94
1.80/1.33
2.15/1.59
M4
1.2810.94
2.90/2.14
4.10/3.02
4.95/3.65
M5
2.50/1.84
5.75/4.24
8.10/5.97
9.70/7.15
M6
4.3/3.1
9.9/7.3
14/10.3
16.5/12.1
M7
7.1/5.2
16.5/12.1
23/1
6.9
27/1
9.9
M8
10.5/7.7
24/1
7.7
34/25 40/29
M10
21/15
48/35
67/49 81/59
M12
36/26
83/61
117/86.2
140/103
M14
58/42
132/97
185/136 220/1
62
M16
88164
200/1
47
285/210 340/250
M18
121/89
25/202
390/287 470/346
M20
171/126
390/287
550/405
660/486
M22
230/1
69
530/390
745/549
890/656
M24
295/217
675/497
960/708
1140\840
M27
435/320
995/733
1400/1032
1
680/1
239
M30
590/435
1350/995
1900/1
401
2280/1
681
M33
800/590
1830/1349
2580/1
902
3090/2278
M36
1030/759
2360/1
740
331
0/2441
3980/2935
M39
1340/988
3050/2249
4290/3163 5150/3798
8.8
10.9 12.9
(Fine Thread)
Nm~ft.lb.
TORQUE
Ma
Nmlft.lb.
Nmm.lh.
M8x1
25/18
35/25 42/30
M10x1.25
49/36
68/50 82/60
M12x1.25
88/64
125/92
150/110
M14x1.25
140/1
03
195/143 235/1
73
M16x1.5
21
0/154
295/217
350/258
M18x1.5
305/224
425/313
51
0/376
M20
x1.5
425/313
600/442
720/531
M22
x1.5
570/420
800/590
960/708
M24
x
2
720/531
1000/737 1200/885
METRIC
CONVERSION
FACTOR:
One
Nm(Newton Meter)
.7375
Foot
Pound;
One
Foot
Pound
1.355818
Nm
FIGURE
5
-2
4-99
5-20-01
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20M
SERVICE
AND MAINTENANCE
MANUAL
AN/MS
STANDARD
BOLT,
NUTS TORQUE
TABLES
FINE-THREAD SERIES
TENSION-type
SMEAR-type TENSION-type
SMEAR
-type
BOLT/NUT
AN()
BOLTS
AN()
BOLTS
NAS()
BOLTS
NAS()
BOLTS
SIZE
AN365/AN310
AN364/AN320 AN365/AN310
AN364/AN320
8-36
12-15 7-9
10-32.
20-25 12-15
25-30
15-20
1/4-28
50-70
30-40. 80-100
50-60
5/1
6-24
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
9/1
6-18
800-1 000
480-600
1100-1300 650-800
5/8-18
1100-1300
600-780
1250-1
550 750-950
3/4-16
2300-2500.
1300-1500
2650-3200 1600-1
900
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
9000-11
000 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
160-1 85
95-1 00
7/16-14
235-255
140-155
1/2-13
400-480
240-290
9/16-12
500-700 300-420
5/8-11
700-900
420-540
3/4-10
1150-1600
700-950
7/8-9
2200-3000.
1300-1
800
TORQUE
VALUES
(Units
are
Inch-pounds)
Figure
5 3
Reference:
Federal Aviation
Agency
Advisory
Circular No.
43.13
1(A),
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
’Yriction
drag
torque"
to
the recommended
torque
value
from
Figure
5-2.
This
value
is
considered "Final
Torque
Value".
(FRICTION
DRAG
TORQUE
REC’MD
TORQUE
FINAL
TORQUE).
CAUTION
DO NOT REUSE
LOCKNUTS
IF
THEY
CAN
BE
RUN
UP
FINGER
TIGHT.
5-20-01
4-99
10
OLDWILLWAYNE

SERVICE AND MAINTENANCE MANUAL M20M MOONEYAIRCRAFT CORPORATION
5-20-02
-AIRCRAFT FILE
INSPECTION
5-20-05
50-HOUR
INSPECTION
-(Repetitive)
Aircraft 100-hour
and
annual
inspections
cover,
in
The
50-hour
inspection
includes
all
requirements
of
the
addition
to
examining
the aircraft
proper,
a
review
of
25-hour
inspection, plus
the
necessary
removal of
the
status
of
compliance
with
current
Federal
Aviation
inspection
doors,
panels,
or
fairings.
After
the
first
25
Regulations.
This review
includes
inspection
of
the
hours of
operating
time,
a
new,
remanufactured,
or
Airplane Flight
Manual,
Aircraft
Log
Book,
Engine Log newly
overhauled
engine
should be
given
a
50-hour
Book,
Propeller
Log
Book,
Registration
Certificate,
inspection
including
replacement
of the
lubricating
oil
Airworthiness
Certificate,
Weight
Balance
Record,
and filter.
Engine
Service
Information,
Aircraft
Radio
Station
1.
Engine.(Refer
to
engine
manufacturer
service
data
License
(if
applicable),
FAA Airworthiness
Directives,
SE #408A
or
subsequen,
for
oil
change
frequency)
and
Mooney
service
documents.
A.
Drain
engine
oil
sump
5-20-03
ENGINE FUNCTIONAL
CHECK
B. Remove
and
clean
suction
oil
strainer;
reinstall
Prior
to
a
scheduled
100-hour
or
annual
inspection,
strainer
and
plug. Safety
wire strainer
plug.
and/or
25
hours
after installation
of
new
or
overhauled
C. Remove
and
replace
the
full-flow oil filter
engine,
wash down the
engine
and
engine
cartridge.
components.
Then
perform
an
engine
runup
in
accord
with
procedure
recommended
in
the
Airplane
Flight
D. Drain
and clean
fuel
strainer.
Manual.
Make
a
record
of
all
malfunctions
and
E.
Remove
and clean
fuel
injector
fuel
strainer.
abnormalities. After the
engine
runup,
complete
a
differential
(hot
engine)
compression
check.
To
verify
F.
Service
engine
oil
sump
with
proper
type,
grade,
correction
of malfunctions and
abnormalities,
perform
a
and
amount
of
lubricating
oil.
second
engine
runup
and
a
flight
test
after
completing
G.
Inspect
ennine
intake
and
e~haust
systems
for
the
inspection.
evidence
of
lea~kage
and looseness.
Reference
Lycoming
Service
Instruction
No.
1422A
or
subsequent
5-20-04
FIRST 25-HOURS
INSPECTION
revision
~br
exhaust
and
TIT
inspection
procedures.
The,
one
time,
25-hour
inspection
consists
of
a
visual
H.
Inspect
spark
plug
elbows
and
shielding
nuts
for
inspection
of
the
propeller,
engine,
and
aircraft
general
security.
condition,
including
a
preflight
inspection
as
outlined
in
the
Airplane Flight
Manual.
The
inspection
does
not
I.
Inspect cylinders
for evidence
of
overheating.
require
removal of
all
access
panels
or
disassembly
of
J.
Inspect
turbocharger
for
security
of
clamps
and
components;
however,
it should include
completion
of
attachments.
all
lubrication
8
service
requirements.
The
inspection
K.
Inspect
baffles for
secure
anchorage,
close fit
should be extensive
enough
to
detect
any
damage
or
around
cylinders,
and freedom from cracks.
maladjustment
which
might
jeopardize
flight safety.
After
the
first
25
hours
of
a new or
overhauled
engine
L.
Inspect
engine
controls
for
full
travel,
freedom
of
operation,
refer
to
paragraph
5-20-05
for the
movement,
and
security.
recommended
engine
inspection.
M.
Visually Inspect
fuel and oil lines
for
security
of
1.
Visually inspect
propeller,
spinner,
and
engine
co""ections and evidence of
leakage
or
damage.
cowling;
remove
cowling.
N.
Visually
inspect
induction
air
system;
check
2.
Inspect
and clean induction air
filter if
aircraft
has
operation
of
alternate-air door
(refer
to
paragraph
been
operating
under
dusty
conditions. Check
71-62-00).
operation
of
alternate
air door.
2.
Propeller.
3.
inspect
engine
compartment
for
evidence
of
fuel,
A.
Inspect
propeller
hub and
spinner
for
general
oil
or
exhaust leaks.
condition, looseness,
and/or
oil
leakage.
4.
Inspect security
and
condition
of
equipment
B.
Inspect
blades
for
nicks
and
cracks.
Repair
prior
installed
on
engine.
to next
Right.
5.
Inspect
fuselage, wing
and
empennage
for
3.
Cabin.
extemal evidence
of
damage.
Pay particular
attention
A.
Inspect
brake and
parking
brake
control
to
scratches and dents.
systems
for
proper
operation
and
fluid
level.
6.
Inspect
windshields and
windows
for
crazing,
cracks,
and scratches.
B.
Inspect
trim
system
and indicator
for free
operation
and travel.
7.
Inspect
control
systems
for
binding,
excessive
freeplay,
and
damage.
C.
Inspect
cabin and
baggage
doors
for
damage,
proper
operation,
and
sealing.
8.
Inspect pitot
and
static
systems
for
possible
obsbuctions.
D.
Inspect
cabin,
instrument
panel,
glareshield,
position,
anticollision,
landing
and
taxi,
lights.
9.
Inspect
aircraft
exterior
for
security
of
bolts,
E.
Inspect
fuel selector
valve,
gascolator,
and
screws,
etc.
boost
pump
for
proper
operation.
10.
Inspect
and service
batteries.
4-99
5-20-02
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20M
SERVICE
AND
MAINTENANCE MANUAL
F.
Inspect
oxygen
system
(tf
installed).
C. Drain
engine
oil
sump;
remove,
inspect
and
4.
Landing
Gear.
clean
oil
suction
screens;
reinstall
and
safety.
Remove
full-flow
oil
filter
cartridge;
replace
with
new
cartridge
A.
Inspect
´•tires for
cuts,
blisters,
wear,
and
proper
and
safety.
Inspect
crank
case
breather
lines for
inflation.
obstruction.
Safety
wire
oil filter
installation.
B.
Inspect
shock
discs
for
proper
extension
at
D.
Refill
engine
oil
sump
with
the
proper
type,
aircraft
static
weight.
grade,
and
quantity
of
lubricating
oil.
C.
Inspect hydraulic
brakes for
wear,
warpage
and
E.
Inspect
fuel
injector
and all
fuel
line connections
proper
installation.
for
security
and
condition.
5.
Wings.
F.
Remove and
inspect
gascolator
strainer,
A.
Inspect
surfaces
and
tips
for
damage.
reinstall
strainer.
Inspect
fuel lines
and
connections:
B.
pressure
check
fuel
system
with mixture control
at
Inspect
ailerons,
aileron
attachments,
and
IDLE
CUTOFF
and
BO~ST
PUMP
ON.
bellcranks
for
damage
and
proper
operation.
G.
Inspect
all
air
ducting
and connections
in the
C.
Inspect flaps
and attachments
for
damage
and
heating
and
induction
air
systems
for leaks.
Remove and
proper
operation.
clean
induction
air
filter
(replace
at
500
Hrs). Inspect
D.
Lubricate
controls
per
Section
5-20-07
if
altemate
air door
and
magnet
for
security
and
operation.
necessary,
Leak
check ail
exhaust
manifold
connections,
engine
6.
Fuselage
and
Empennage.
exhaust
manifolds.
Inspect
for
security.
A.
Inspect
stabilizer,
elevators,
fin,
and rudder for
H´•
I"spect magnetos
for
grounding
and
damage
and
proper
attachment.
synchronization;
Inspect magneto
points
for
condition,
clearance,
and
timing.
Inspect
distributor
block
for
B.
Lubricate
controls
per
Section
5-20-07
if
erosion
and cracks.
Inspect
cam
follower
felt for
proper
necessary.
lubrication,
and
remove
excessive
oil
from breaker
C.
Inspect
Trim
System
for
proper
operation.
compartment.
Inspect
magneto
pressurization
per
Slick
magneto
maintenance
manual.
Repair
or
replace
7. See
Section
5-20-07
for
any
repetitive
50
hour
components,
if
required.
inspections
and
component
service
guide.
I.
Inspect
baffles for
secure
anchorage,
cracks,
5-20-06
100-HOUR
or
ANNUAL
holes,
deformation,
and
for close
fit
around
cylinders.
INSPECTION
Inspect
cylinders
for
burned
paint
and
cracked
or
(Refer
to
Fig. 54)
broken
fins.
Inspect
baffle sealant.
The
100-hour
(or annual)
inspection
is
a
thorough,
J.
inspect
accessory
case,
starter,
aitemators,
vacuum
searching inspection
of
the entire
aircraft.
Preparation
pumps
hose,
firewall
and
fittings
for
security
or
damage.
for
the
inspection
includes
the
thorough
cleaning
of
K.
Inspect
turbocharger
for cracks
or
damage.
exterior
and
engine
compartment,
removal
of all
Inspect
turbocharger
control
components
for
obvious
fuselage,
wing,
and
empennage
inspection
doors,
damage.
Inspect
intercooler
for
damage
or
obstruction.
cover
plates,
and
fairings
at
all
systems
attach,
hinge,
and
bearing
locations
(including
wing
and
empennage
L.
Inspect
tubular
engine
mount
for
cracks,
to
fuselage
mating
points).
Operating
limit
replacement
damage
or
corrosion;
check
all bolts
and
rubber
(See
Section
5-10-01)
and
special
testing
of
isolation
mounts
for
security
and
condition.
components
is
to
be
included
at
this interval
when
M.
inspect engine
and
propeller
controls
for
free
applicable.
Comply
with
applicable
FAA
Directives,
AD
operation,
full
travel,
proper
connection
(security)
of
Notes,
and
applicable
Mooney
or
Vendor
mandatory
cable
housing
swage
at
the
HEAD tube and
security
of
Service
Bulletins
and
Instrudions.
Check
for
aircraft
attachment.
conformance
to
FAA
Specification
2A3.
NOTE
Recommended
100-hour/annual
and
special
inspection
Cablecraft control
cables
are
lubricated
for
the
requirements
are
outlined
in
the
following
paragraphs:
life
of
the
control cable. DO
NOT
REMOVE seals
1.
ENGINE
INSPECTION.
Prior
to
the
inspection,
or
lubricate
control
cable.
remove
the
engine
cowling
and
propeller
spinner.
N.
Inspect
enaine
fuel
pump
pressure.
(See
Wash
down
the
engine
and
engine
compartment.
Then
Textron-Lycoming
Service
information
and
Section
perform
an
engine
runup
in
accord
with the
procedure
71-00-50
for
this
procedure).
recommended
in
the
Engine
Maintenance and
Operators
Manual.
To
verify
correction
of
malfunctions
O.
Inspect
and
reinstall
cowling.
Check cowl
flap’s
and
abnormalities,
perform
a
second
runup
and
flight
for
operation,
condition,
proper
opening
and
position
test
after
the
100-hour/annual
inspection
engine
indication.
set-up.
P.
Inspect
battery
cables,
electrical
wiring,
and
A.
Complete
a
differential
(hot
engine)
ignition
harness
for
condition,
secure
anchorage,
loose
compression
check:
clean
andgap
or
replace spark
tenninals,
and burned
or
chaffed insulation.
plugs
if
necessary.
Q.
Inspect
batteries,
battery
mount
areas,
and
vent
B.
Inspect
engine
for evidence
of
excessive
fuel
or
system
for
condition and
corrosion.
Inspect
blast tube
oil
leakage.
Inspect
oil cooler.
Inspect
oil fuel
hoses
for obstruction.
Flush
battery
mount
areas
with
soda
for
condition
security. Repair
as
required.
solution
to
neutralize
corrosive action
if
necessary.
5-20-06
4-99
12
OLDWILLWAYNE