Mooney M20S 1998 Installation and user guide

SERVICE
A~19
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~T
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E Y
AIRC
RBFT C
O
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ATIO
~J
LOUIS
SCHREINER FIELD
ECERRVILLE,
TEXAS 780~8
ORIGINAL
NOV.,
1998
MANUAL
NUMBER
iao
OLDWILLWAYNE

MOONEY
AIRCRAFT
COPORATION
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
in-
stalled
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
from vendors
and
utilized
on
the
applicable
Mooney
Aircraft
Model(s)
addressed
in
this
publication.
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20S
SERVICE AND MAINTENANCE
MANUAL
LCIG [1F REVISIONS
Always destroy
superseded
paaes
when
you
insert
revised
DP1TE OF SECTIONS DATE
OF
SECTICINS
REVISION
AF~FECTED
REVISION
AFFECTED
NOT
EI
A list
of effective
oaaes
will
aDoear
at
the
keainnina
of
each
chaDter,
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20S
SERVICE AND
MAINTENANCE MANUAL
INTRODUCTION
CHAPTER
(System)
This
manual
provides
servicing
and
maintenance
in´•
The
various
groups
contain
major
systems
informa´•
formation
for
the
Mooney
Model
M20S,
Serial
Num´•
tion
such
as
flight
controls,
landing
gear,
etc.
The
bers
30-0001 and
ON.
Maintenance
actions
that
re-
systems
are
arranged
numerically
per
%AMA
recom´•
fer
to
a
limited
number
of aircraft will
be
designated
mended
number
assignment,
It is
suggested
for
ex´•
by
serial number
of
applicable airplanes, ample,that
"Fuel"
be
identified
with~ the
Chapter
number
"28’.
The
sequence
of
numbers,
28-00´•00,
The Part
Number’s
of
replacement
or
repair
parts
refers
to
the
General
information
of
the Fuel
Sys´•
should
be
identified
using
the
Illustrated
Parts
%ata´•
tems.
log
~applicable
to
Model
and
S/N
of
aircraft
being
worked
on.
The
correct
P/N
can
be
ordered
through
SECTION
(Sub-System)
any
Mooney
Service
Center.
See SECTION
91 for
ex-
ceptions
on
Electrical
Components.
The
major
systems
of
an
aircraft
are
broken
down
into
sub-systems.
These
sub-systems
are
identified
The format
and
contents
of this
manual
are
prepared
by
the
second element of
the
sequence
of
numbers,
in
accordance
with
GENERAL
AVIATION
MANUFAC-
re.,
28´•20´•00.
The element
´•20- indicates
the
distri´•
TURER’S ASSOCIATION
(GAMA)
bution
portion
of
the
fuel
system.
Specification
No.
2.
The
manual is
supplemented
SUBJECT
(Unit)
with
wiring
schematics
for
the various
model
year
airplanes,as
necessary.
These
are
located
in
enve´•
The
individual
units
within
a
sub´•system
may
be
lopes
at
the
back
of the
manual
texts
pages.
identified
by
a
third element of
the
sequence
of
num´•
bers,
ie.,28´•20´•01.
This number
is
assigned
by
the
NOTE
manufacturer
and
may
or
may
not be used
depend´•
Revisions
or
reissues
of
this
manual
are
ing
upon
the
complexity
of
the
maintenance
action
not
automatically provided
to manual
recommended.
holders.
Holders
of
these
and
other
Mooney
APPLICATION
OF NUMBERING
SYSTEM
Technical Publications
should
complete
the
information
on
the
"YELLOW
CARD’’
located
Mooney
Aircraft
Corporation
is
in
the
process
of
re´•
at
the
front
of
the
Title
Page
and send
to
vising
all
applicable
maintenance technical
publica´•
Mooney
Aircraft
Corporation,
Louis
tions
to
GAMA
format.
When
this
effort
is
completed
Schreiner
Field,
Kerrville,
TX., 78028,
Attn:
any
publication
concerning
maintenance of aircraft
Service Parts
Department.
will conform
to
this
basic
Any
person
wishing
information
concerning
the
Fuel
Dis-
Notification
is
sent
to
known
manual
holders
when
tribution
System
would
refer
to
the
pages
identified
another manual
is
prepared
to
replace
the
subscrip-
as
,28´•20-00,
in
any
maintenance
onented
publica´•
tion and
advises
that
no more
revisions will
be
sent
tion.
These
pages
will
be
numbered
sequentially
out.
The
new
manual
will
require
a
new
subscription
within
each
system
breakdown
in
the
current
Moo´•
service.
If
additional
Technical
Publications
are
de-
ney
series
of
aircraft.
As
Mooney
aircraft models
be´•
sired,
contact
the above
department
at
Mooney
Air´•
come more
complex
the
page
numbers
may
be
se´•
craft
Corporation
at
(830)
896-6000,
ext.
2092.
quentially
numbered
within
sub-systems.
Correspondence concerning
maintenance
or
part
The
table
of
contents
in
the
front of
each
Chapter
will
numbers
on
an
airplane
should
contain
the
aircraft
provide
a
list
of
systems
and/or
subjects
covered in
model
num
ber and
serial number. The serial
number
the
Chapter.
For
example:
appears
on
the
identification
placard
located
on
the
aft
end,
left
hand
side
of
the
tailcone
below the
hori´•
zontal
stabilizer.
28´•00
General
28-10
Storage
(Tanks,
vents,
repair,
ASSIGNMENT
OF
SUBJECT
MATERIAL
etc.)
28´•20
Distribution
:e~eel:ontent
of
this
publication
is
organired
at
four
(Boost
pumps,
fuel
lines,
etc.)
Group
28-40
Indicating
Chapter(System)
(Sender
Units,
quantity
Section
(Sub´•system)
gauges,
etc.)
Subject (Unit)
If
there
is
a
reason
to
distinguish
between
LEFT
HAND
or
RIGHT HAND
fuel
quantity
sending
units
GROUP
then the number
would
be
expanded
to
28~40´•01
(Left
Hand)
and
28-40-02
(Right
Hand).
This
concept
These
are
primary
divisions
of
the manual that
en´•
will
apply
to
any
expanded
information
throughout
able
broad
separation
of
content, ie.,
Airframe
sys-
the
publications.
tems
VS
Powerplant
systems.
These
groups
are
identified
by
tabs.
INTRODUCTION
INTRODUCTION´•1
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MAN UAL
M20S
MOONEY AIRCRAFT
CORPORATION
SUPPLEMENTARY
PUBLICATIONS
The
following
list of Manufacturers and/or
publications
can
provide servicing
and maintenance information
on
components
of the
Mooney,
Model
M20S. 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.
Any~eublications
available
from
Mooney
Aircraft
Corporation
are
listed in the Parts
Price List
and
are
available
through
any
Mooney
Service Center.
Most
manufacturer/vendor
publications
are
not
availabel
through
Mooney
Aircraft
Corporation,
these should
be
obtained
from
the
applicable
Manufacturer/Vendor.
As
publications
on
various
components
become
available,
they
will be
added
to
the list
below.
VENDOR ADDRESSES
PUBLICATIONS
ENGINE
PUBLICATIONS
The
following
maintenance
publications
can
be
obtained
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,
Form X30568A.
Illustrated Parts
Catalog
for
Teledyne
Continental
Motors
10-550
series aircraft
engines,
Form X30569A.
Maintenance
Operators
Manual
for
Teledyne
Continental
Motors
10-550
aircraft
engines,
Form
X30565.
Service
Bulletins
Specify
model of
enginefor
which
maintenance
data is desired
when
ordering.
Fuel
Injector
Manual,
Form X30593A
ACCESSORY
PUBLICATIONS
PROPELLER
McCauley
Propellers
Obtain
publications
from
McCauley
Accessories
Division,
3535
McCauley
Drive,
Van-
dalia,
0~.,45377.
Service
Manual No. 780630
for
McCauley
C200
series
constant
speed propellers.
MAGNETO
Teledyne
Continental
Motors,
Aircraft
Products,
P.O. Box
90,
Mobile,
Alabama,
USA,
36601,
Attn: Publi-
cations
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, Mobile, 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:
Publi´•
cations
Dept
IGNITION
SYSTEM
Master
Service
Manual,
TCM
Ignition
Systems
and
Components,
Form
X40000,
Teledyne
Continental
Mo´•
tors,
Aircraft
Products,
P.O.
Box
90,
Mobile,
Alabama,
USA,
36601,
Attn: Publications
Dept
SPEED
BRAKES
Precise
Flight,
Inc.,
63120
Powell
Butte
Rd., Bend,
OR
97701,
Telephone:
(503)
382-8684
INTRODUCTION-2
INTRODUCTION
OLDWILLWAYNE

MOONEY AIRCRAfT
CORPORATION
M20S
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
WEIGHING
00
LEVELING
9
TOWING AND TAXIING
00
GROUND
HANDLING
10
TOWING
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
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
60
TEMPERATURE
CONTROL
24
ELECTRICAL
POWER
00
GENERAL
30
DC
GENERATION
40
EXTERNAL POWR
50
ELECTRICAL
LOAD
DISTRIBUTION
INTRODUCTION
INTRODUCTION-3
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20S
MOONEY
AIRCRAFT
CORPORATION
CHAPTER
SECTION TITLE
25
EQUIPMENT/FURNISHI
NGS
THISSECTION
MAYNOTBE
00
GENERAL
INCLUDED
IN
THIS
S M.
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
STATIC AIR
PRESSURE
SYSTEM
20
DIRECTIONAL GYRO
COMPASS
I
NTROD
UCTI
ON
´•4
1
NTROD
UCTI
ON
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20S
SERVICE
AND
MAINTENANCE
MANUAL
CHAPTER
SECTION
TITLE
35
OXYGEN
THIS
SECTION MAY NOT BE
00
GENERAL
INCLUDED
IN
THIS
S
M.
10/20
CREW/PASSENGERS
37
VACUUM
00
GENERAL
10
DISTRIBUTION
20
INDICATING
30
REPAIR
40
OPERATIONAL
PROCEDURES
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
10/20
WINDSHIELD
CABIN
WINDOWS
50
PLEXIGLASS DRILLING
57
WINGS
00
GENERAL
10
MAIN
FRAME
20
AUXILIARY
STRUCTURE
30
PLATES/SKINS
40
ATTACH
FITTINGS
50
FLIGHT SURFACES
INTRODUCTION
INTRODUCTION-5
OLDWILLWAYNE

SERVICE AND
MAINTENANCE
MANUAL
M20S
MOONEY AIRCRAFT
CORPORATION
CHAPTER
SECTION
TITLE
60
STANDARD
PRACTICES
PROPELLERS
61
PROPELLERS
00
GENERAL
10
PROPELLER
ASSEMBLY
20
CONTROLLING
40
BALANCING
PROCEDURES
71
POWERPLANT
00
GENERAL
10
COWLING
20
MOUNTS
30
FIRESEALS
60
AIR I
NTAKES
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
30
PRESSURE INDICATING
78
EXHAUST
00
GENERAL
10
INSTALLATION
30
EXHAUST SYSTEM
40
REPLACEMENT COMPONENTS
79
OIL
00
GENERAL
10
STORAGE
20
DISTRIBUTION
30
INDICATING
40
TRANSDUCERS
50
TROUBLE SHOOTING
80
STARTING
00
GENERAL
10
CRANKING
INTRODUCTION-6
INTRODUCTION
OLDWILLWAYNE

MOONET
AIRCRAFT
CORPORATION
M20S
SERVICE
AND
MAINTENANCE
MANUAL
CHAPTER
SECTION
TITLE
81
TURBINES
THIS
SECTION
MAY NOT BE
00
GENERAL
INCLUDED
IN THIS
S
M.
91
SCHEMATICS
00
GENERAL
20
ELECTRICAL SYSTEM
HARDWARE
CHARTS
30
SCHEMATICS
95
SPECIAL
EQUIPMENT
INTRODUCTION INTRODUCTION-7
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20S MOONEY AIRCRAFT
CORPORATION
BLANK
INTRODUCTION-8
INTRODUCTION
OLDWILLWAYNE

CHAPTER
TIME,
LIMITSI
MAINTENANCE
CH EC
KS
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20S
MOONEY
AIRCRAFT CORPORATION
CHAPTER
5
TIME
LIMITS/MAINTENANCE
CHECKS
LIST
OF EFFECTIVE
PAGES
CHAPTER
SECTION
SUBJECT
PAGE
DATE
5-Effectivity
1/2BLANK. 11-98
5-Contents
3/4BLANK.
11-98
5-00´•00 5.
11-98
5-10-00
6.
11-98
5-20-01
7.
11-98
5-20-01
8.
11-98
5-20´•01
9.
11´•98
5-20´•01 10.
11-98
5-20-02
11.
11´•98
5-20-06
12.
11-98
5´•20´•06
13.
11-98
5-20-06 14.
11-98
5-20-06
15.
11-98
5-20-06
16.
11-98
5-20-07
17.
11-98
5´•20´•07
18.
11´•98
5-20-07
19.
11-98
5´•20-07
20.
11-98
5-EFFECTIVITY
1/2BLANK
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20S
SERVICE
AND
MAINTENANCE
MANUAL
CHAPTER
5
TIME
LIMITS/MAINTENANCE
CHECKS
TABLE
OF
CONTENTS
CHAPTER
SECTION
SUBJECT
SUBJ
ECT
PAGE
5´•00-00
General.
5
5´•00´•01
Landing
Gear
System
5
5-00-02
Flight
Control
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
Ventilating
Sy;tems
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
6
5-20-01
Check
Points,
Torque
Values
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
5-CONTENTS
3/4BLANK
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20S
MOONEY AIRCRAFT
CORPORATION
5-00-00
GENERAL
5-00-04
ELECTRIC
POWER
SYSTEM
AIRCRAFT
DESCRIPTION.
The
M20S
series of
i.
The
Master
Switch
and
power
relay
control
the
aircraft
are
four
place,
high-performance,
normally
electrical
power
system,
comprised
of
a
100
AMP,
aspirated,
single-engine,
low-wing
monoplanes.
The
28
Volt,
alternator
and
two
10
AMP
HR,
24
Volt,
all´•metal
airframe
has
a
tubular´•steel
cabin frame
batteries.
The alternator
system
has
an
overvoltage
covered
with
nonstructural
aluminum
protective
relay
and
an
overvoltage
annunciator
skins,
a
light.
Circuit breakers
or
circuit
breaker
switches
semi´•monocoque
tailcone,
and
a
full-cantilever,
laminar´•flow
wing.
Control
surfaces
have
structural
electrical
wiring
and
equipment
from
spar
construction
with
stressed
skins
riveted
to
the
Standard
electrical
equipment
includes:
2´•100
watt
spars
and ribs.l)ual
control
wheels
accompany
the
landing lights,
2´•100;
watt
taxi
lights,
navigation
pedals
have toe
brakes
linkedilot’s
rudder
conventional
flight
controls.
The
individual
lights,
interior
lights,instrument
panel/glareshield
hydraulic
cylinders
that
supply
pressure
to
the
lights,
gear
and
stall
warning
system,
an
electrical
hydraulic
dlsc
brakes
on
each
main
gear
wheel.
fuel
boost
pump,
an
electric
starter,
an
electric
Removable,
co-pilot
rudder
pedals
are
standard
gear
retraction/extension
system,
with
manual
extension
override,
an
electric
trim
system
equipment.
The
tricycle
landing
gear,
having
a
(optional)
and
an
electrical
flap system.
steerable
nose
wheel
controlled-bX~udder
pedalwide-span
5-00-05
-INSTRUMENTS
action,
is
fully
ret
ra
cta
ble.
trailing-edge
wing flaps
are
electrically
operated.
For
stabilizer
trim,
the
entire
empennage
pivots
All
flight
instruments
are
in the
shock-mounted
co-pilot’s
instruments
are
in
the
vertically
about its
points.
Flight
Panel.
pitot
system
provides
air
pressure
to
operate
the
airspeed
indicator.
The
5-00-01
LANDING
GEAR
SYSTEM
instrument
static
pressure
system
has
two
static
The
electric
landing
gear
system
has
a
steerable
air
pickup
ports
tone
on
each
side
of
the
tailcone)
that
open
to
the
atmosphere.
An
alternate
static
nose
wheel.
Single
disc
self-adjusting
hydraulic
source
is
provided
on
center
console.
The
brakes
are
featured
on
the
main
gear.
Gear
instrument
panel/glareshield
lighting
systems
have
position
lights,
a
warning
horn
and
a
gear
position
manual
dimming
mechanisms.
Indicator
on
the
ii
oorboa
rd
are
sta
ndard
equipment.
Bungee springs
that
preload
thethe
5-00-06
CABIN
HEATING
VENTILATING
retraction
mechanism
In an
over-center
position
SYSTEMS
lock
the
gear
down.
An
air
pressure
actuated
safety
switch in
the
electrical
system
prevents
electric
The heater muff
encasing
the exhaust
system
is the
gear
retraction
on
takeoff
until
a
safe
flying
speed
cabin
heat
source.
Hot air from
the heater
muff,
is
attained.
A
gear
throttle
warning
horn
sounds
mixed
with
ambient
air,
controls
cabin
when
the
manifold
pressure
is
less
than
a
pre´•set
temperature.
Air
routed
from
the main heater
duct
value
with the
landing
gear
up.
The
electric
gear
system
to
nozzles
at
the
windshield base
defrosts
retraction
system
has
a
manual
extension
system
the
windshield.
An
optional
defrost
blower
motor
connected
to
the
gear
actuator
that
permits
system
is
available.
manual
lowering
of
the
gear
in
the
event
of
an
5-00-07
FUEL
SYSTEM
electrical malfunction.
Landing
gear
doors
fully
enclose
the wheel
wells
to
reduce
sound levels
ana
The
fuel
system
has
sealed,
integral
wing
tanks
in
increase
performance.
the
forward,
inboard
section
of each
wing.
Vents
at
the
aft,
outboard
top
corner
of
each
tank
vent
through
a
NACA
scoop
on
the
lower
wing
surface.
5-00-02
FLIGHT
CONTROL
SYSTEMS
Fuel
sump
drains
are
at
the
lowest
point
in
each
The
dual
flight
control
systems
can
be
operated
tank.
The electric
fuel
pump
is in
the
bottom
left
from
eitherthe
pilot
or
co-pilot
seat.
All
flight
forward section
of
the
fuselage,
aft
of
the
firewall.
controls
are
conventional
in
operation,
using
The
engine-driven
fuel
pump
mounts
on
the
engine
pushpull
tubes
to
link the
control
surfaces
to
the
crankcase. Two
fuel
quantity
transmitters
in
each
tank
are
wired
in
series
to fuel
quantity
gauges
in
control
wheels and
rudder
pedals.
Formica
guide
blocks
ma
i ntai
n
cent
rol
tube
alignment
and
the
engine
cluster
gauge.
The
Master
Switch,
left
dampen
vibration.
An
interconnect
spring
side of
the
pilot’s panel,
activates the
fuel
qua
mechanism
links
the
aileron
and rudder
systems
to
indicating
systems.
The
optional
visual
assist
in
control
coord i
nation.
The
standard
gauges
are
for
partial fueling
of
wing
tanks..
co-pllot’s
rudder
pedals
are
removable.
A
dual
A
"low
fuel"
warning
annunciator
light
for
each
bra’ke
installation is
optional
for the
co´•pilot’s
tank is
activated
when usable
fuel
quantity
goes
position.
The
manual
or
electric
trim
system
sets
below 2
1/2
gallons.
the horizontal
stabilizer
angle
of attack.
5-10-00
TIME
LIMIT
COMPONENTS
5-00-03
WING
FLAP
SYSTEM
It is
recommended
that
overhaul
or
replacement
of
components
should
be
accomplished
not
later
than
Wing
flaps
are
electrically
actuated
and
are
the
specified
period
of
operation
for
that
controlled
by
a
spring
loaded
"up-off-down"
switch
component
or
in
accordance
with manufactures
on
the
center
console.
service
data
or
airworthiness directives.
5-00-00
OLDWILLWAYNE

MOONN AIRCRAFT CORPORATION
M20S 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
requiring replaced
or
overhauled
when
inspection
or
maintenance,
performance
reveals
an
unserviceable
condition.
5-10-01
OVERHAUL
MAINTENANCE
AND
REPLACEMENT
SCHEDULE
ITEM
RECOMMENDED
OVERHAUL,
MAINTENANCE
OR REPLACE
LlME
UMITS
Landing
Gear
Actuator No-Back
Spring
1000
Hours
Avionics
See
SI
M20-52A
Plessey
(GEC)
See
SI
M20-92A
All other
Components
On
Condition
Powerplant
Engine
2000Hours
Propeller
2000Hours
or
6
years
(refer
to
repairdata)
Magnetos
-T~M’
500Hours
(referto
repair/inspection
data)
Induction
Air Filter..
500
Hours
All other
Components
OnCondition
Fuel
011
System
Fuel
Selector Valve
(Airight
or
Christopher
Tool)
On
Condition
Flexible
Hoses
(All, except
Teffon
as
below)
7
years
or
Engine
O/H,
whichever
occurs
first.
All other
Components (includes
Teflon
hoses)
dn
i=ot;dit’ion’
Instruments
Vacuum
Regulator
Garter
Filter
100
Hours
Filters-Vacuum
Pump
500
Hours
(CV1J4
Filter-
On
Condition)
Filters
Gyro
Instruments
500
Hours
or
Annually
Other
Components
On Condition
Electrical
System
All
Components
On Condition
Flight
Controls
SDeedbrakes
1000Hours
(See27-96-00)
All
OtherComponentF;
On
Condition
Miscellaneous
Systems
Vacuum
Pump, Primary
On
Condition
or
500
Hrs.
Engine
O/H
Stand-by
Vacuum
Pump/Cl;tch
200
Hours
[Inspsct
Drive
Coupling)
E.L.’T.
Battery
2
Years
or
1
Hour
Total
Use
Oxygen
Cylinders
Lt.
Wt. Steel Cylinders
5
yrs.(O/H)
/24
years
or
10,000
recharge cycles
Replace
Composite
Cylinders.
6
yrs.(O/H)
/15
years
or
10,000
recharge cycles Replace
Scott
Oxygen Regulator
6
years-overhaul;
3
years-test
Air
Conditioning Components
~ee
Section
21-5800 for
specific
maintenance
and
servicing
times.
All
Other
Component~
(Excluding
Avionics)
On
Condition
(See
NOTE
above)
Avionics
Refer
to
Manufacturers
Publications
Hydrostatic
Test
Required
S
year
intervals.
NOTE
Components
should
be
Inspected
and
serviced at
regular
Intervals
per
the
servicing,
lubrication
end
Inspection
chart
of this
manual.
5-10-00
OLDWILLWAYNE

SERVICE
AND
MAINTENANCE
MANUAL
M20S MOONEY
AIRCRAFT CORPORATION
5-20-00
SCHEDULED
MAINTENANCE
Oxygen
Lines Use
only
MIL´•T´•5542
thread
CHECKS
compound
or
Teflon thread seal
tape
on
threads
of
Inspection
Intervals.
Perform
a
25,
50,
or
100´•hour
valves, connectors,
fittings,
parts
or
assemblies
inspection
of
the
ai
rcraft,
com
ponents
and
engi
ne
which
might
come
in
contact
with
oxygen.
The
at
recommended intervals
as
outlined in
the
th’ead
compound
must
be
applied
sparingly
to
the
following
paragraphs.
first three threads
of
the male
fitting
only.
No
compound
is
to
be used
on
the
coupling
sleeves
or
NOTE
on
the
outside
of
the tube flares.
Extreme
care
Aircraft
operated
in
a
salt air environment
are
should
be
exercised
to
prevent
the
contamination
considered
high
risk
for
corrosion
damage,
of the
thread
compound
or
teflon
tape
with
oil,
and
should
he cleaned and
inspected
af
grease
or
other lubricant.
frequent
intervals.
Refer
to
A%
43-4.
Fuel,
Hydraulic,
Air,
Oil
Lines
Use
"Parker
Thread Lube"
or
equivalent
on
male
fittings only.
5-20-01
INSPECTION
CHECK
POINTS
Apply
lubricant,
omitting
the first
two
threads,
The
general points
to be
covered
during
inspection
sparingly
and
carefully.
are
grouped
in accordance
with the
nature
and
Engine Fittings
Use
only
aircraft
en~gine
oil
to
function
of the items discussed,
lubricate
fittings
threaded
directly
to
engine.
Vacuum
Lines
No
lubrication
is
to
be used.
i.
Moving
Parts shall
be
inspected
and
checked
as
applicable
for:
proper
operation,
security
of
Check
manufacturers
instructions
when
installing
attachment,
sealing,
cleanliness,
lubrication,
components.
Refer
to Section
37
for maintenance
servicing,
safetying,
adjustment,
tension,
travel,
p’ocedures
on
vacuum
systim.
condition
of
hinges,
binding,
excessive
wear,
Tapered
Threads
Use
Teflon
Threadseal
Tape.
cracking,
corrosion, deformation,
and
any
other
(1)
Continue
to
tighten
until
fitting
is
correctly
apparent
damage.
positioned
but
do
not
overrun or
backoff.
2.
Metal Parts shall
be
inspected,
as
applicable, (2)
If
leaks
are
detected,
tighten
one
full
turn
for:
security
of
attachment,
condition
of
finish
more.
and/or
sealant,
distortion,
fatigue
cracks,
welding
(3)
If leaks
persist,
the
parts
should
be
cracks,
corrosion,
and
any
other
apparent
damage,
disconnected
and
rejected;
replace
with
new
The tubular
frame structure
should
be
inspected
components.
during
each
annual
inspection
for
any
signs
of
corrosion
or
damage.
5.
Bolts
and
nuts
in critical
areas
shall be
inspected
for:
fretting,
wear,
damage,
stretch,
3.
Fuel,
air,
oil and
hydraulic
oil lines
and
hoses
proper
torque,
(Figure
5´•2)
and
safetying.
shall
be
inspected
as
applicable
for:
cracks, dents,
kinks,
deterioration,
obstruction,
chaffing,
6´•
Electrical
wiring
shall
be
inspected
as
improper
bend
radius,
and
insecure
installation.
applicable
for:
loose,
corroded,
and
broken
Replace
or
correct
if
any
of
these conditions
exist,
terminals;
chaffed, broken,
and
worn
insulation;
Hose
clamp
installations
on
fuel
and
hydraulic
insecure
installation;
heat
deterioration;
and
any
systems
between
systems
or
between
systems
and
Other
apparent
damage.
the
engine
shall
be
torqued
to 25 inch
pounds.
7. Filters
and
screens
shall
be
removed,
cleaned
Hose
clamp
installations
on
blast
tubes,
air
ducts,
and
inspected
for
contamination
or
damage
that
vacuum
Ilnes drain
and
vent
lines shall be would
require replacement.
torqued
to
15
jnch’
pounds.
4.
Pipe
Threads
Tightening
and
torque
procedures.
Lubricate
pipe
threads
as
follows:
TORQUE
VALUES
See
Following
Tables.
5´•20´•00
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20S
SERVICE
AND
MAINTENANCE
MANUAL
FLARE
NUT
TORQUE
VALUES-
Tighten
to
minimum
torque
value
for
appropriate
site
as
shown
(Figure
5-1).
CAUTION
These
torque
values
are
derived from
oil-free
cadmium-plated
threads.
FITTING
SIZE
ALUMINUM
TUBING
STEEL TUBING
TORQUE
INCH
POUNDS
MINIMUM
MAXI~IUM
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
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
screwassemgld~
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
Hardware
(Black
Finish)
Friction
Coefficient
0.14
NOMINAL 5.6
8.8
PROPERTY
10.9
12.9
DIAMETER
CLASS
(Coarse
Thread)
Nm/ft.lb.
Nm/ft.lb.
TORQUE
Ma
Nm/ft. Ib.
Nm/ft.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
10.4/7.6
M6 4.6/3.3
10.5/7.7
15/11
18/13
M7 7.6/5.6
17.5/12.9
25/18.4
29/21.3
M8 11/8.1 26/19
36/26
43/33
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
95/70
215/158
305/224
365/269
M18
130/95
295/217
420/309
500/368
M20
184/135 420/309
590/435
710/523
M22 250/184 570/420
800/590
960/708
M24
315/232
725/534
1020/752
1220/899
M27
470/346
1070/789
1510/1113
1810/1334
M30
635/468
1450/ 1069
2050/1511
2450/ 1806
M33
865/637
1970/1452
2770/2042
3330/2455
M36
1111/819 2530/
1865
3560/2625
4280/3156
M39
1440/ 1062 3290/2426
4620/3407
5550/4093
5-20-01
OLDWILLWAYNE

SERVICE AND
MAINTENANCE
MANUAL
M20S
MOONEY AIRCRAFT
CORPORATION
(METRIC
TORQUE
TABLES
CONTINUED)
NOMINAL
8.8
PROPERTY 10.9
12.9
DIAMETER
CLASS
(Fine Thread)
Nm/ft.lb.
TOROUE
Ma
Nm/ft.lb.
Nm/ft.lb.
M8
x
1
27/19
38/28
45/33
M10
x
1.25
52/38
73/53
88/64
M12x1.25
95/70
135/99 160/118
M14x1.5
150/110 210/154
250/184
M16
x
1.5
225/165
315/232
380/280
M18
x
1.5
325/239 460/339
550/405
M20
x
1.5
460/339
640/472
770/567
M22
x
1.5
610/449 860/634
1050/774
M24
x
2
780/575
1100/811
1300/958
TIGHTENING
TORQUES
Electrically
Zinc Plated Hardware Friction Coefficient
0. 125
DIAM ETER 5.6
8.8
PROPERTY
10.9
12.9
(Coarse
Thread)
CLASS
Nm/ft. Ib.
Nm/ft.
Ib.
TOROUE
Ma
N
m
/f
t.
I
b.
Nm/ft. Ib.
M3 0.
56/0.41
1.28/0.94
1.80/1.33
2.15/1.59
M4
1.28/0.94
2.90/2.
14 4.10/3.02
4.95/3.65
M5 2.5011.84
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
23/16.9
27/19.9
M8 10.5/7.7
24/17.7
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
88/64 200/
147
285/210 340/250
M18
121/89
25/202 390/287 470/346
M20 171/126
390/287 550/405 660/486
M22
230/169
530/390 745/549
890/656
M24
295/217 675/497
960/708 1140\840
M27 435/320
995/733 1400/1032 1680/1239
M30
590/435
1350/995
1900/
1401 2280/1681
M33
800/590 1830/
1349
2580/ 1902
3090/2278
M36
1030/759
2360/1740
3310/2441 3980/2935
M39
13’40/ 988 3050/2249 4290/3163
5150/3798
NOMINAL
8.8
PROPERTY
10.9
12.9
DIAMETER
CLASS
(Fine
Thread)
Nm/ft.lb.
T_OROUE
Ma
Nm/ft. Ib. Nm/ft.lb.
M8
x
1
25/18 35/25 42/30
M10
x
1.25
49/36
68/50
82/60
M12
x
1.25
88/64 125/92
150/110
M14
x
1.25
140/103 195/143 235/173
M16
x
1.5
210/154
295/217
350/258
M18
x
1.5
305/224
425/313 510/376
M20
x
1.5
425/313
600/442
720/531
M22
x
1.5
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
5-20-01
OLDWILLWAYNE

MOONEY
AIRCRAFT
CORPORATION
M20S
SERVICE
AND
MAINTENANCE
MANUAL
AN/MS STANDARD
BOLT,
NUTS
TORQUE
TABLES
FINE-THREAD
SERIES
TEN
S
ION
-type
SHEAR´•type
TEN
SION
´•type.
SMEAR
´•type
NUT/BOLT
AN()
BOLTS
AN()
BOLTS.
NASC)
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
80-100
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´•1000
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
5/16-18
80-90
48-55
3/8-16 160´•185
95-100
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 1300-1800
TORQUE
VALUES
(Units
are
Inch´•pounds) Figure
5´•2
Reference:
Federal
Aviation
Agency
Advisory
Circular No.
43.13´•lA,
p.
118
Recommended
Torque
Values for Nut´•Bolt combination
(Units
are
inch´•pounds)
i.
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
REC’MD
TORQU.E
FINAL
TORQUE).
CAUTION
DO
NOT
REUSE LOCKNUTS
IF THEY
CAN
BE
RUN UP
FINGER
TIGHT.
5-20-01
10
OLDWILLWAYNE