Mooney M20M Reference manual

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SUBJECI:
MOONEY
24
VOLT AIRCRAFT ELECTRICAL
WIRING
MODIFICATION,
1
(Revision
A
is
applicable
to M20J and
M20K
aircraft
only
and
is
still
in
effect for
those model
aircraft.
Revision
B
is
applicable
to
M20M
only--).
MODEUS/N
AFFECTED:
MOONEY
MODEL:
M20M
S/N
27-0001
THRU
27-0052
TIME
OF
COMPLIANCE:
AT NDCT
SCHEDULED MAINTENANCE
INTRODUCTION:
THE
24
VOLT
ELECTRICAL
SYSTEM iS WIRED
IN
A
MANNER THAT
RENDERS
THE
OVERVOLTAGE
WARNING
LIGHT
IN THE
ANNUNCIATOR
PANEL
ASSEMBLY
INOPERATIVE
SHOULD
AN
ALTERNATOR
OVERVOLTAGE
OCCUR.
THIS
S.
B.
PROVIDES
INSTRUCTIONS
TO
REWIRE
A
PORTION OF
THE
CIRCUTT
TO
ENABLE
THIS WARNING LIGHT.
INSTRUCTIONS:
1. Disconnect
voltage
regulator
(for
Altemator
#1)
iocated
under
the instrument
panel
on
the
co-pilot’s
side.
2
Locate existino
~Mre
number
M-PA13A18;
push
wire
out
of
pin
8
of
#1
regulator
main
harness
receptacle.
3.
Cut
pin
from
wire,
M-PA13A18;
cap
wire
end
using
AMP
324485
wire
cap
(included
in
kit).
4.
Remove
Glareshield
per
instructions
in
the
appropn’ate
S M
manual,
Section
39-10-01.
5.
Insert
wire
number M-PA13B18
(included
in
-1B
kit)
into
pin
8
of
voltage
regulator
receptacle
and
reconnect
regulator.
6.
Route
wire
number M-PA13B18
along existing
wire bundle
to
annunciator
panel
connector
(M-WT103A).
Secure
with
lacing
cord
or
TyRaps.
7.
Locate
wire
number M-WT02A20 connected
to
pin
1
of annunciator
panel
connector,
M-WT103A,
and
cut
M-V1~02C\20
wire
6
inches back from
connector.
8.
Use
AMP
320559
wire
splice
to
re-connect
wire
number
M-WT02A20 and
tile
unconnected
end of
new
wire
M-PA13B18
(SEE
nGUREM20-245-1B).
9.
For
No.
2 Altemator:
repeat
Steps
1
through
5
with
#2
regulator
but
on
wire numbers
M-PA33A18
(Steps
1,
2
3)
and
M-PA33B18
(Step
5);
Route unconnected end
of
wire number
M-PA33B18
to
vacuum
switch
on
back
of
Artifical Horhon
and
connect to
"white"
terminal.
10.
Remove the
1
amp
Annunciator
C/B
and
replace
with the
2
amp
C/B,
included
in -1B
kit.
1
I.
Functionally
check
operation
of
altemator(s)
per
POH/AFM,
Section
IV,
Normal
Procedures,
Before Takeoff
12.
Enter
compliance
note
in
aircraft
logbook
and
return
aircraft
to
service.
WARRANIY: This
kit should be
ordered
from
the
Mooney
Service Center in
your
area.
Normal
warranty
billing
policies
will
be
in
affect
for
this kit.
MooneyAircraft
Corporation
will
allow
up
to
2.0
hourslabor
to
accomplish
this
modification
if
a
completed
Warranty
Claim
is
received
within
180
days
from the
date of this
SeM’ce
Bulletin.
REFERENCE
DATA:
N/A
PARTS LIST:
KIT
P/N
SB-M20-245-1B
(M20M only)
mM P~
DESCRIPTION
.QK
1.
M-PA~3B18
WIRE
ASSEMBLY
1
2
M-PA33B18
WIRE
ASSEMBLY
1
3. 324485
WIRE
CAP
(AMP)
2
4.
320559
WIRE
SPLICE
(AMP)
1
5.
7277-2-2
C/B,
ANNUNCIATOR
(2 AMP)
1
FI
GURESI
TABLES:
SPUCE
-I
I
FIGURE
M20-24518
(M20M
only)

THIS
SERVICE
BULLETIN
IS
FAA
APPROVED
FOR
ENGINEERING
DESIGN.
SUBJECT:
MOONEY
TLS,
M20M.
INCREASED
TAKEOFF
WEIGHT RETROFIT
MODEL
S/N
AFFECTED:
MOONEY
MODEL
M20M.
SIN 27-0001
THRU
27-0052
TIME
OF
COMPLIANCE.
AT
OWNERS
DISCRETION
BUT
MANDATORY
IF
AIRCRAFT IS
TO
BE
FLOWN
AT
A
TAKEOFF
WEIGHT
ABOVE
3200
POUNDS.
INTRODUCTION:
Some aircraft
owners
have
expressed
a
desire to increase the
useful
load
of the
M20M
aircraft.
Mooney
Aircraft
Corporation
is
offering
the
retrofit
procedures
of this
Service Bulletin
to
accomplish
this.
There
are
several
areas
that
will
be
modified
in order
for
the aircraft
to
be
flown
at
the
increased
takeoff
weight
of
3368
pounds.
It
is
recommended
that the
aircraft
be
brought
back
to
Mooney
Aircraft
Corporation
for-the retrofit.
Scheduling
of the
retrofrt
action
will
be co-ordinated
by
the
Product
Support
Department,
telephone
(512)
896-6000.
INSTRUCTIONS:
I. Remove
and
replace
the Main
Landing
retraction
truss
assembly,
P/N
520024501
(UH)
and
-502
(R/H)
per
M20M
Service
and
Maintenance Manual
(S
M)
No.
150,
Section
32-10-00.
The
new
truss
will
be
identified
by
an
"A-2"
metal
stamp
on
the
fork
lover
center
link)
and
a
ink
stamp
"A-2"
after
paint.
2.
Check
for
proper
operation
and
rigging
of
landing
gear
retraction
system
after
replacement
of
retraction
truss
assembly
per
S
M
No.
150.
Section
32-30-00.
3.
Remove
the
8
ABS
flap
hinge
fairings.
(4
on
each
wing) by drilling
out
the rivets
on
fairing
flanges
and the
side rivet
on
each outboard
fairing.
The
two
inboard
fairings
have
screws
attaching
them
to
the
fuselage
belly
fairing
and
one
screw
(inboard
side)
attaching
ABS
fairing
to
the
inboard
wing flap hinge
arm
aluminum
fairing.
All
ABS
flap
hinge
fairings
will
be modified
pn~or
to
re-installation.
(See
Step
4
below)
4.
Remove
flap
gap
seals,
P/N
210374-001
(1
pc)
-003
(2 pcs),
from
left
wing
and
P/N
210374-002
(1
pc)
-004
(2
pcs),
from
right
wing by:
(1)
Dn’ll
out
the
lower
forward
row
of rivets
holding
forward
edge
of aluminum
gap
seal
on.
(2)
Lowerfiaps,
drill
out
row
of
rivets
holding
aluminum
channels,
P/N
210375-1
(1 pc)
and
-003
(2
pcs)
from
each
wing
(Reference
Figure
SE
M20-248-1).
Remove
the
flap
gap
seals
with
the
channels
still
attached.
5.
The AVEX
1601-0401
rivets
being
drilled out
will
leave
portions
of the
rivet inside the
wing.
THESE
NEED
TO
BE
REMOVED.
Enlarge
the
existing
No.
30
hole
outboard
of
each
aft rib
(rib
rivet line
can
be
seen
on
wing
skins)
to
a
.250
hole
(8
holes
on
each
wing). Forcefully
use
hand
or
rubber
malletto
hit
wing
skin
area
(DO
NOT
DAMAGE
SKINS)
and
a
magnet
to
move
rivet
residue toward
.250
hole and
remove
all
pieces,
with
magnet,
through
hole.
This should
be
done
between
each
rib
bay.
6.
After
all
drilled
rivet
residue
is removed. Install A10-80 R’Nnuts
in
each
enlarged
hole.
(16
places)
7.
Trim
ABS
flap hinge fairings.
P/N
210398-005
(LH)
-006
(RH)
(1
each
side)
inboard,
P/N
210379-009
(LH)
-010
(RH) (2
each
side)
mid,
and
P/N
210379-011
-012
(1
each
side)
outboard,
per
Figures
SE
M20-248-2A
8r
28.
8.
A
new
hole
will
be
required
in
outboard ’side wall"
of each
middle
ABS
fairing,
now
to
be
identified
as
P/N
210379-013
(LH)(2
ea)
074
(RH)(2
ea)
to
match
tooling
hole
in
the
two
middle
wing
flap hinge
arm
aluminum
fairings,
P/N
210106,
(L
R
wing).
Reference
Figure
SE
M20-248-3 for basic instructions
to
drill holes.
1
9.
NOTE:
Outboard
hole
of
middle 8
inboard
iairings
will
require enlarging
to.189
(No.
12
hole)
so
M835207-263
screw
can
be used
in
the
A10-80
rivnut
to
secure
fairing fiange.
Re-install each
modified
fairing
using appropriate
existing
rivet holes
in
wing
skins that match
remaining
hole
in
flange
of
each
ABS
hinge
fairing
and
new
hole
to
match
tooling
hole
in
wing
flap
hinge
arm
fairings.
Use
AVM
1601-0410
(or equivalent)
blind
rivets
and
MS35207-263
screws
to
attach
ABS
fairings.

SE
M20-248
DATE
3
20
90
Page
2
of
4
10.
Use
AVD:
1
601-0410
rivets
(59
each
row,
minus
ABS
fairing
attach holes
and
enlarged
holes
for
rivnuts))
to
fill
remaining
holes
in
wing
skins
drilled
out
dun’ng
removal
of
gap
seals and channels.
Reference
Figure
SE M20-248-1.
1
1.
install
MS35207-263 screws
in
all
other
enlarged
holes
to
seal
up
wing
skin
area.
CTotal
of
(16)
MS35207-263
screws
are
required
for all
enlarged
holes.)
12.
Repainting
of
the
now
exposed
wing
flap
gap
area
will
be
required.
Contact
Mooney
Service
Parts
Department
for
paint
color
PIN
for
aircraft
Sen~al
Number.
13.
Remove
existing
airspeed
indicator,
P/N
820308-527,
and
replace
with
new
airspeed
indicator,
P/N
820308-531,
included
inthis
kit;
it
incoporates
new
airspeed markings
for the
increased
weight performance.
14.
After
airspeed
indicator
has
been
replaced
and all
lines
secured,
perform
pitot/static
check
for
leaks.
15.
Remove the
OPERATING
UMITATIONS
placard
from
pilot’s
side
panel
and
replace
with
new
OPERATING
UNIITAIIONS
placard,
P/N
150080-980,
included in
kit.
16.
Enter
compliance
note
in
AVC
log
book,
insert AFM
Supplement
into
POH/AFM
and
return
aircraft
to
service.
WARRANTY:
Mooney
Aircraft
Corporation
will
perforn
all
retrofit
action
at
the
factory
service
facility.
Aircraft
owners
will
need
to
contact
the
Product
Support
Department,
(512)
896-6000
to
make
arrangements
for
scheduling
aircraft.
REFERENCE
DATA:
N/A
PARTS
LIST:
KITPARTNUMGER
SE
M20-248-1
ITEM
P/N
DESCRIPTION
QT/.
i.
520024-501
(A-2)
RETRACT TRUSS
ASSY,
LH
1
2.
520024-502
(A-2)
RETRACT TRUSS
ASSY,
RH
1
3.
820308-531
AIRSPEED INDICATOR
1
4.
150080-980
PLACARD
1
5. 1601-0410
RIVET.
AVEX
240
6.
Al
0-80
RIVNUT
.16
7.
MS35207-263
SCREWS
.16
8.
NIA
AFM
SUPPLEMENT SE
M20-248 1
FIGURES/
TABLES: See
Figures
on
next
pages.

SE M20-248
DATE3-20-90
Page
3
of
4
MS20600AD4
(67
PLCS)
REPLACE
WITH
16019410
AVEX
RIVETS
DRILL
THIS ROW
OF
RIVETS
OUT.
240014
FLAP
ASSY
210375
CHANNELS
MS20470AD4
(61
PLCS)
~210374
DO
NOT
DRILL
THESE
RIVETS
OUT.
MS20600AD4
FLAP
GAP SEALS
(61
PLCS)
EXTEND
FLAPS
AND
DRILL
OUT
UPPER
ROW
OF
RIVETS
REPLACE
WITH
1601-0410
AVEX
RIVETS
HOLDING
CHANNELS
ON.
DRILL
MIS
ROW
OF
RIVETS
OUT.
FIGURE
SE M20-248-1
TRIM
EXISTING
ABS
FAIRINGS
TO
DIMENSIONS
SHOWN.
DOTrrD
LINES
INDleArr
UNTRIMMED
CONFIGURAT;IPH
3-CS
~.Z5
\.2J
I
-009
(SHOWN)
210379 FAIRINGS
’------I
-011
(SHOWN)
-olo
(092)
-012
(OPP)
t
OFa\n\NC~>
NEW
CONFKiURATION
PIK
FA\RI~G
OPP
FIGURE
SE
M20-248-2A

SE
M20-248
DATE
3 20
90
Page
4 of
4
FAIRING
Slu2-I
210398-005(SHOWN)
-006
(gpp)
t
0-~
o~c;
NEW
CONFIGURATION
PIK
FIGURE SE M20-248-28
i/
~VLX
160~-M\D
(J)
,*L~C
4P~C
I I I V I
klS35207-263
1´•11
C.12~
DI~
~o
LY
Z1010CI
’~b
L~
Wow
hv~x
-14
OCe
16019410
Rtvrr.
-F
I I~-ts
-I~
w
-\4´•
orr
U.L
--IcO~o
*LI
~LI-
Izcn~
COD~\huo
UP)
~De
FIGURE
SE
M20-248-3

SUBJECT: MOONC/
M20M
ENGINE
MOUNT
HEAT
SHIELD
MODEU
SIN
AFFECTED:
27-0001
THRU
27-0129
TIME
OF
COMPLIANCE:
WITHIN
NMT
50
OPERATING
HOURS
INTRODUCTION:
There have
been occasions that
the
engine
mount,
in
the
vicinity
of
the
turbocharger,
has
had
paint
scorched
or
missing
due
to
exhaust
temperatures.
The
steel
tubing
may
show
evidence
of
heat
and
in
need of
maintenance
action.
The
heat
shidd
and
associated
components
on
this
kit
will
reduce
this
temperature
related
action.
INSTRUCTIONS:
1.
Remove
upper
and lower
ccwling
per
M20M
S
M,
Section
71-10-00.
2
Locate
the
area
of the
engine
mount
as
shown.
(See Figure
SE
M20-251-1 for
location)
3.
Inspect
all
engine
mount
tubes
in
dose
proximity
to
the
for
evidence of heat
related
damage.
Re~iir
any
damage
per
appropriate
AC43-13
procedures
or
M20M
S M
manual,
Chapter
51.
4.
Lightly
sand,
and
repaint
with
high
temperature
paint,
any
tubes
showing
evidence
of heat.
5.
Install
630071-001
shield
using
two
each
630071-003
damp
assemblies and
appropriate
attaching
hardware.
(Reference Figure
SE
MM251-1 for
proper
location and orientation
on
the
engine
mount
tube.
6.
Re-install
lower
and
upper
cowling
per
M20M
S
M,
Section 71-11-00.
7.
Enter
compliance
statement
in
Aimame
log
book
and
retum
aircraft to service.
WARRANP~
Mooney
Aircraft
Corporation
will allow
up
to
0.7
hours labor to install
the
components
of this
kit
The
kit
can
be ordered
through
the
nearest
Mooney
Service Center.
Warranty
credit
will be
allowed
forthe
kit
if
necessary
paperwork
is
received
by
Service
Parts
within
180
days
of
the
date
of
this
Service Bulletin
REFERENCE
DATA
N/A
PARTS USTr
KIT PART
NUMBER -SB M20-251-1
ITEM
P/N,,....
DESCRIPTION
.QTY
1.
630071-001
SHIELD
1
2
630071~03
CLAMP
ASSY 2
3.
AN3-6A
BOLT 2
4.
AN960-10 .WASHER 4
5.
MS21
042-3
NUT 4
FIGURESI
TABLES:
REFER
TO FlGURE SE
M20-251-1

I;
~-ci.
-T
T
SERVICE
BULLETIN
M20-251
DATE:
4-10-92
Page
2
of
2
n
i´•/´•l~
590048
ENGINE
NOUNT
CUUP ASSY.
530071-003
(2
REOWRED)~
~t
0.00
SHIELD
MM1M2-3
HUI
AN950-10
WASHER
/-530071-001
SHIEU)
TOP
VIEW
630371-003
Ifi~
590048
PICINE .UOUNI
~2 REaVatEO)
-~3
sylml-atn 4lmo
AN3-6A
BOLT
AN860-10
WASHER
MS21042-3
NLIF
I
SECTION
A-A
ROTATED
550 PUIEIE OF
~GINE LIDUNI TUBE
ii i
1-
ii~----_,
~iRREWW.
(RD)
630135 WL
PIPE
d
-i
~Jm
V
´•ti
SIDEVIEW
FIGURE
SE
M20-251-1

SUBJECT:
M20M LANDING
GEAR RIGG)NG INSPECTION
AND
MODIFICATION.
MODEU
S/N
AFFECTED:
M20M
S/N 27-0107
THRU
27-0147
(S/N’s
27-0115,
27-0123,
27-0127,
27~131,
27-0137,
27-0142,
27-0144,
27-0150
HAVE HAD
INSTRUCTIONS
OF SE
ACCOMPLISHED).
TIME
OF
COMPLIANCE:
WlTHlN
NMT
25
FLIGHT HOURS OR
AT NDCT
SCHEDULED
MAINTENANCE.
Some
aircraft
within
the above
S/N
block have
experienced
landing
gear
inner-door malfunc-
.tions. This
has
not caused
difficulty
with
the
retraction/extension
cycle
in
any
of the
cases.
Maintenance
inspec-
tions have found that
some
of the
mechanism
components
have
gone
beyond
normal
tolerance.
Replacement
of
some
ofthe
components
is
recommended. To eliminate the
possibility
of
exceeding
tolerances,
a
mechani-
cal
stop
has been
developed
to be
installed in the wheelwells. The
instructions of
this
Service Bulletin and
and
components
of SE Kit
wilt
allow field
personnel
to
retrofit
applicable
aircraft.
INSTRU~TIONS:
i.
Raise aircraft
on
jacks
per
Service
and
Maintenance
(S
h;l)
manual,
Section
71-10-00.
2
Remove
composite belly
skins
per
S
M
manual,
Section
53-30-00.
3.
Perform
Landing
Gear
dperational
Inspection
per
S
M
manual,~Section
32-30-01,
revised
March,
1993.
4. On
LH RH
main
landing
gear,
replace bearings
(B-47)
and
bushings (914020-161)
in
bellcrank
(2).
Replace
rods
(5), (6),
attaching pins
and
hardware.
Inspect
press
fit
pins
on
bellcranks
2,
3
4;
replace
if
worn.
5.
Re-n’g
entire
landing
gear
system
per
S 3
M
manual,
Section
32-30-02,
revised
March,
1993
if
Operational
In-
spections
showany discrepancies.
NOTE
Instructions
of
this Service
Bulletin
are
to
be used
in
conjunction
with
M20M Service and
Maintenance
Manual,
No.
150
Chapter
32,
revised, March,
1993.
When
landing
gear
system
has been
n’gged
and
preload correctly
set,
the inboard
landing
gear
door is
to
have
a
mechanical
stop
incorporated
into the
system
per
the
following
instructions:
6.
Aircraft still
on
jacks.
Landing
gear
down and locked.
7.
Locate the
two
rivets
on
LH RH
whedwells that
are
just
forward of
the inboard
gear
door
hinge
(9)
attaching
rivets
(Ref. Fig M20-254-1).
This
is the location
for the
550075-501
stops
(7)
to
be installed.
8.
Disconnect Inboard
Gear
doors.
Carefully
drill
off
the
two
rivet heads
on
LH RH
sides;
punch
rivets
out.
NOTE
550075501
stop
(7)
has
two
#40
pilot
holes
in
flange.
In
some
instances,
doe
to
manofacturing
toleran-
ces,
the
pilot
holes
may
not
align
exactly
with
both drilled holes
in
wing
rib.
If
this is the
case,
determine
which ofthe
two
holes
in
stop
fiange
viill
create
the better
alignment
of
the
stop
bolt head
(8)
with
the
bellcrank
(4)
arm.
Use
this
hole
as
the
’primary"
attachment hole,
9.
Drill
"primary"
attachment
hole
to size
(i5~20 dn’ll)
in
each
stop.
Cleco
stops
(7)
in
place,
at
"primary"
attach
hole
only,
so
head
of
bolt
(8)
in
stop
aligns
with
arm
of
inboard
gear
door bellcrank
(4)
that
spring
(1)
is
attached
to.
NOTE
It
is
acceptable
to
chamfer
rear
edge
of
Range,
on
stop,
that
rests
against
wing
rib
if
bucked
heads of
rivets
interfere
with
proper
alignment
of
stop
bolt head and bellcrank
arm.
Chamfer
only
as
required
to
clearrivet.
10.
When
stop
(7)
is
decoed in
proper
position,
drill
second
attach
hole
in
stop Range
to
size
(#20
drill), by
back
drilling through
e>dsting
"non-primary"
rivet hole. Deburr
hole
in
Range
and cieco
in
position.
Make
sure
head
of
bolt
(8)
in
stop
aligns
(directly
centered)
with
arm
of bellcrank
(4).

SERVICE
BULLETIN M20-254
DATE:
4-1-93
Page
2
of
4
lNSTRUCTIONS:
(con’t)
11.
Rivet
stops t/),
P/N
550075-501,
in
each
wheelwell
at the
location descn’bed
in
steps
8
9
above
using
rivets
included
in this kit.
Re-attach
Inboard
Gear
doors
before
cycling landing
gear
for
following
steps.
12
Leave
spring
(1)
attached
to
clevis of
inboard
door
bellcrank
(4).
Bolt
head
(8)
should
be screwed
all
the
way
in.
NOTE
Two
mechanics
(personnel)
may
be
required
for the
next
several
steps.
One
under the
aircraft and
the
other
inside
the aircraft
operating
the
landing
gear
switch.
13.
Retract
landing
gear
using
safety by-pass
switch
(See
S
M,
Section
32-30-01,
steps
5, 6,
7)
until
inboard
gear
door has
traveled
as
far
as
it
willgo during
its
retraction
cycle.
In
this
position,
the
pivot
points
of
bellcrank
(3)
center
line
of
rod
-(5)
will
be
in
a
straight
line
(Reference
Figure
M20-254-2). Components
(2),
(5)
(6)
should
now
be in
a
loaded
condition
and feel
very
tight.
14.
Adjust stop
bolt head
(8)
OUT until
it
rests
on
bellcrank
(4)
arm.
Continue
to
adjust
bolt
head
OUT
until
rods
(5)
gr
(6)
become
loose
(no
load felt
on
either
rod).
Bellcrank
(2)
will
also become loose
when bolt
head
(8)
is in
correct
position.
Tighten
jam
nut
on
bolt
(8)
against
tube
on
stop
(7).
15.
Repeat
installation of
stop (7) (Steps
7
thru
11)
and
adjustment procedures (Steps
12 thru
14)
in
other
whedwdl.
16.
Cycle
landing
gear
through
five
complete
retraction/extension
cycles; inspect
all
components
during
and
after
cycles
for
any
interference,
binding
or
improper
operation.
Reference
Operational
Inspection
in
S
M,
as
done in
Step
No.
3.
17~
Ccmplete
lag
boole
entry
and
retum
aircraft
to
service.
WARRANP~
Mooney
Aircraft
Corporation
will
allow
3.0
hours labor
to
comply
with this
Service Bulletin.
Parts
Kit will
be
ordered
through
Mooney
Service
Centers
and credit
will
be issued
upon
receipt
of
warranty
forms within
180
days
of the issue date of this
Service
Bulletin.
REFERENCE
DATA:
N/A
PARTS
UST:
KIT PART
NUMBER SBM20-254-1
lTEM
.P/N
DESCRIPTION
QTY
1
~550075601
STOP
ASSY.
.2
2
.550082-503
ROD,
LOWER
.2
3
.550082-505
ROD,
UPPER
.2
4
.91 4020-1 61
BUSHING
.2
5
.8-47
BEARING
.2
6
.MS20392-2C7
PIN,
CLNIS
(PRESS
FIT:BELLCRANK
4)
.2
7
.MS20392-2C9
PIN,
CLNIS
(PRESS
FIT-BELLCRANK i&
3)
.4
8
.MS20392-2C17
PIN,
CLEVIS
.2
9
.AN381-2-6
PIN,
COTTER
.8
10.
.AN470AD5-13 RIVET
.4
11.
M20M S
M
Chapter
32,
kevised 3-93’
.1
At
some
later date the
complete
S
M will
be
revised
and
Chapter 32,
as
revised
in
March,
1993,
will
be
available
to
the field
and
may
not
be included
in
this Service
Bulletin
kit.
FlGUREl
TABLES: SEE
NDCT
PAGES FOR
FlGURES
SBM20-254-1
AND
SBM20-254-2

SERVICE
BULLETIN
M20-254
DATE:
4-1-93
Page
3
of
4
p’’
O
spi~P
a
dp"‘’
3~
o~ a
o
a
a,
a
I! \~4
5~
11 I ~\o
2 --~21 I,I II
al II
61 0\
L.9
SBM20-25
4´•-1

SERVICE
BUU-FTIN
M20-254
DATE:
4-1-93
Page
4 of
4
NI7I1CE
THESE PIVDT P[71NTS ARE
IN
ALMOST
A
STRAIGHT
LINEI
THIS
R-EPRESENTS
THE
M[7ST EXIREME
TRAVEL THAT
THESE
CDMP
ONENTS
SHOULD BE,
i
o
SBM20-254-2

SERVICE
BUU~ETIN
M20-255A
I
ISSUEDATE:
Novemberl’l,
1993
SUB3ECT:
Mooney
M20M,
Retrofit,
cabin
exhaust
vents
on
fuselage
sideslcabin
ventilation
system
modifiction.
MODELSISIN
AFFECTED:
PART
1:
M20M
S/N
27-0002
THRU
27-0137
(D(CEPT
S/N
27-0094)
PART
2:
M20M
SM
27-0053
THRU
27-0167
(EXCEPT
S/N
27-0094)
I
PART
3:
M20M
SRN
27-0002
THRU
27-0052
TlME
OF
COMPLIANCE:
Within
next
25
Right
hours
or
at
next
scheduled
maintenance action.
INTAODUCTION:
In
order
to
provide
a
continual
purge
of the cabin
air,
compliance
of this Service
Bulletin
needs
to
be
accomplished
for
serial
numbers listed
above.
INSTRUCTIONS:
PART
ADDCABIN
D(HAUSTVENTS
(F1G.SBM20-255-1)
(S/N
27-0002
thru
27-0167,
excluding
S/N
27-0094)
I
1.
it
is
recommended,
but
not
essential,
to
remove
aft interior
baggage compartment
ABS
panels,
both
sides.
The
long
ABS
panels,
forward
of
the
baggage
campartment
panels,
will
need
to
be
pulled
UP
and
restrained
UP
to
provide
access
to
the
inside
skin.
These
long
ABS
panels
may
be
removed,
if
desired,
to
accomplish
the
retrofit
Caution should
be
observed
during
cut
out
of
hole
and
drilling
of
rivet
holes
in
fuselage
skin
soas
not
to
drill
through
any
electrical
wiring,
ABS
panels
or
tubular
structure.
Z
Locate
area
of
fuselage
skin
to
be
cut
out
by
measuring
from
the
baggage
campartment/cabin
area,
vertical
skin
lap,
forward,
9.0
inches and
dawn
16.4
inches
from lower
edge
of
ah window
skin
clrt-out.
The size
of each
cut-out
should
be
29
inches
high
and
2.26
inches
wide.
Keep
vertical sides
of
cut-out
parallel
with
vertical
skin
lap.
Recommended radius
on
all
comers
of
cut-out
is
.125
inches.
(Fig.
SE
M20-255-1)
3.
Deburrcut-out
4.
Cleco
640296-001
ABS baffle
to
a
lowered
plate
for
UH
side
sub-assembly
to
verify
that all
pilot
holes
in baffle
and
lowered
plate
are
matched. Drill
all
pilot
holes
out to
#30
holes.
Repeat
for
R/H
side
sub-as-
sembly.
Ident~y
lowered
plates
as
RIH
and
UH
during
this
procedure.
NOTE:
Be
sure
that
louvers
will have
openings
toward the aft end of the aircraft.
5.
After
drilling
i4~30
matching
holes
in
baffle and
lowered
plate,
sandwich
a
640247-003,
aluminum
screen
between
UH
baffle
and
UH
lowered
plate; punch matching
holes
through
screen
mesh
with
an
awl.
Repeat
for
RIH
side
sub-assembly.
6.
Place
R/H
640130-000
lowered
plate
in
position,
over
RIH
cut-out
hole,
in
accordance
with
Fig.
SE
M20-255-1.The
location of
the
lowered
plate
does not
have
to
be
exact,
however,
a
minimum
of
.31
inr
ches
edge
distance should
be
maintained
for
all fasteners. Drill
#30
holes in
fuselage
skin
to
match
#30
holes in lowered
plates
(13
places
far
each
plate).
Reference
Pig.
SE
M20-255-1.
Repeat
for
UH
cut~ut
hole..
7.
install
RM
lowered
plate
(outside
of
fuselage
skin),
R/H
aluminum
screen
and
640246-002
ABS
baffle
(inside
of
fuselage skin)
with
Avex
1691-0410-05
rivetsand
AN960-6
washers.
Sandwich
aluminun
screen
between
ABS
baffle
and
inside
surface of
fuselage
skin
as
shown
in
Fig.
SE
M20-255-1.
Repeat
for
UH
side.
3.
Clean
up
area
and
install ABS
interior
panels,
ii
remaved.
9.
Paint
rivets,
attaching
lowered
plates,
to
match
exterior
paint
color.
10.
Enter
compliance
note
in
log
book and
return
aircraft
to
service.
Il.
RI
out
and
return
pre-addressed,
stamped
compliance
card.
PART
2:
REPLACE
ASSEMBLY
1N
CABrN VENLlVITION
J-BOX
(FIG.
SE
M20-255-2)
(S/N
27-0053
THRU
27-0167
excluding
SIN
27-0094)
I
1,
Locate cabin ventilation J-Box in
forward,
RH
cabin
immediately
behind
firewall.
2.
Access
J-Box
assembly
by
loosening
QS100-M40S
clamp
at
J-Box
and
flex
tubing
connection;
replace
existing
640326-505
butterfly
assembly
with
new
640326-511
butterfly
assembly, Fig.
SE M20-
255-2
3.
Re-instaI(ffextubingto
J-Boxwith
QS100-M40S
clamp.
4.
Enter
compliance
note
in
log
book and
retum
aircraft
to service.
5.
Fill
out
and
retum
pre-addressed,
stamped
compliance
card.

SERVICE
BULLETIN
M20-255A
ISSUE
DATE:
November
17,
1993
Page
2
of
4
PART
3:
MODIRCATION OF
SUDE
PLATE
ON
CABIN
VENTILATION
J-BOX
(FIG.
SE
M20-2553)
(S/N
27-0002
THRU
27-0052)
1.
Locate
cabin
ventilation
J-Box in
forward,
RH
cabin
immediately
behind
firewall,
2.
Access J-Box
slide
plate
assembly by
loosening
QS100-M40S
clamp
on
J-Box outlet
air
flex
tubing
connection.
Use
needle
nose
pliers
to
remove
MS16562-4
roll
pin
from slide
plate.
Remove cable
as-
sembly/cable
stops
from slide
plate.
Remove
e~dsting
640010-000
slide
platetrom
J-Box.
3.
Modify
640010-000
slide
plate by
dnlling
two
0.50
inch
diameter
holes,
in
locations
as
shown
in
FIG.
SE
M20-255-3.
Slide
Plate
must
now
be
re-identified
as
P/N
SE
M20-255-501;
use
indelible
ink
to
mark
P/N
on
body
of
slide
plate.
4.
Re-install modified slide
plate
into J-Box
assembly.
Attach
cable
assembly
with
existing
cable
stops
and hardware.
5.
Position
slide
prate
so
MS16562-4
roll
pin
can
be
inserted into hole
through
outlet
air
flex tube
opening.
6.
Verify
slide
plate operation
is
smooth
and
complete
travel
can
be
obtained
in
both
directions,
prior
to
installation
of
flex
tubing.
7.
Re-install
flextubingtoJ-Boxwith
QS100-M40S
clamp.
8.
Enter
compliance
note
in
log
book and
retum
aircraft
to
service.
9.
Fill
outand
return
pre-addressed,
stamped compliance
card.
Applicable
kits
should
be
ordered from
Mooney
Service Centers.
WARRANP~
Mooney
Aircraft
Corporation
will
allow
4.0
hours
labor
to
incorporate
applicable portions
of
this
Service
Bulletin
on
AIC
S/N’s
27-0002
TH RU
27-0137
and
1.0
hours labor
on A/C S/N’s
27-01
38
THRU
27-0167
if
compliance
card and
warranty
paper
work is
received from
Service
Center
by Mooney
Service
Parts
Department
within
180
days
of
the
on’ginal
date
(September
29,
1993)
of this
Service
Bulletin.
Normal
warranty
procedures
on
parts
and kit
components
will
be followed.
REFERENCE
DATA:
NIA
PARTS UST:
PART
1-
Kit
Part
Number
-SB
M20-255-1
(S/N
27-0002
MRU
27-0137
U(CEPT
27-0094)
Item ..Part Number
Descn’ption
Quantity
1.
.640130-000,..
Plate,
Louvered
(Painted)
.2
2
,640247-003
Screen,
Aluminum,
(16 mesh)
.2
3. 1691-0410-05
Rivet
(AVD()
26
4
.AN960-6
Washer
26
5.
-64029~-001
Baffle,
ABS,
LH
.1
6.
.640296-002
Baffle, ABS,
RH
.1
7.
Paint
To match
AIC
color
.1
8.
,Compliance
Card
To
be
retumed
to
Service
Parts
.1
NOTE
Matching
paint
will
be
shipped
with
kit.
Provide aircraft
S/N
when
orden’ng
above
kit
part
number.
PART 2
Kit
Part Number-
SE
M20-255-2
(S/N
27-0053
MRU
27-0167,
MCEPT
27-0094)
1.
6$0326-511
Butterfly
assembly
.1
2
.MS35206-226
Screw
.2
3.
Compliance
Card
To
be retumed
to
Service Paris
.1
FIGLERES/
TABLES:
See
Figures
SE
M20-255-1,
SE
M20-255-2 and
SE
M20-255-3
on
following
pages.

SERVICE
BULLETIN
M20-255A
ISSUE
DATE:
November
17,
1993
Page
3
of
4
2.26
o
o
lo\
(INSIDE)
10
~ci
2,90SKIN
BAFFLE
ALUMINUM SCREEN
10
PLATE
1
~I I I I III´•
(CIUTSIDE)
VIEW
LOOKING I)OWN
O
(RH
SHOWU
LH TYPICAL)
O
O
-T~O
O
LOUVERED PLATE
STA
-5,37
c-1
16.4 IN.
TO TOP
SEE
j
ET~GE
OF CUTOUT
\I
9,0 IN,
FRON
SKIN
LAP
TO AFT
EDGE
OF
CUTOUT
(BOTH
SIDES
OF
STA
STA
100,00
53,00
FIGURE 1

Senrice Bulletin
M20-255A
ISSUE
DATE:
November
17,
1993
Page
4 of 4
FLEX
J-BI7X ASS
RH VIEW
LDtlKING
INBOARD
O
O
O
BUTTERFLY
ASSY--,
LMS35206-226
SCREVS <2>
SECURE
WITH LOC-TITE
CV
FIGURE
2
0.50
inch diameter
holes.
640010
SUDE
PLATE
TO
BE
RE-IDEN-
TIRED
TO
SE
M20´•255-501
AFTER
MODIRED
WITH
.625
TWO
0.50
INCH
HOLES
PER THIS ILLUSTRATION.
O
USE
INDEUBLE
(PERMANENT)
INK
ON
BODY OF
?-1
.625
´•u~-
SLIDE
PLATE.
FIGURE
3

THIS
SERVICE
BULLETIN
IS
FAA
APPROVED FOR ENGINEERING DESIGN
SERVICE
BULLETIN
M20-261
ISSUEDATE:
iDecember,
1996
SUBJECT:
BENDU(-MNG SERVICE
BULLETIN
No. SE
KT
76A-7,
JULY/96
(or
later
revision(s)),
KT
76A
ATC
TRANSPONDER
MODELSISIN
AFFECTED:
ALL MODELS OF
MOONC(AIRCRAFT
MANUFACTURED
SINCE
1975
(INCLUDES
M20C,
M20E,
M20F,
M20J, M20K,
M20L,
M20M,
AND
M20FP
AND
ANY
MODEL THAT MAY HAVE
HAD A KT 76A
TRANSPONDER
RETROFI~ED SINCE i
975
(INCLUDES
M20, M20A,
M20B,
M20D,
M20G,
OR
M22)
(APPUES
TO ALL
S/N’s)
TIME OF
COMPLIANCE:
F~EFER
TO
BENDIX-KING
SE
KT
76A-7,
DATED
JULY/96
(or
later
revision(s)
INTFZODUCTION:
i,
Bendix-King
Service Bulletin No.
KT76A-7
provides
information
that
indicates the
integrated
cir-
cuit
(IC)
of
the
KT76A,
P/N
066-1062-00/10!02,
Sn\l’s
from
93,000
to
109,000,
may possess,
or
progress
to,
an
electronic
breakdown
within
the
IC that
causes
either
or
both of the
following
malfunctions:
The
unit
may
incorrectly
interpret
the
output
of
the
encoding
attimeter.
or
2)
The
unit
may
transmit
a
code
other than what
is
set
land shown)
on
the face of the
t~ansponder
unit.
2 The
subject
Bendix-King
SE
provides
the
compliance,
retrofit,
warranty,
and
parts
list information
necessary
for
the
retrofit
procedures
to
be
accomplished by
appropriately
rated
Bendix-King
Seivice Centers.
INSTRUCTIONS: REFER
TO
BENDU(-KING
SE
Kr76A-7,
DATED
JULY/96
(or
later
revision(s)
WARRANPI: I~EFERTO BENDIX-KING SE KT
76A-7,
DATED JULY/96
(or
later
revision(s)
REFERENCE
DATA: ~EFER
TO
BENDD(-KING
SE
KT
76A-7,
DATED
JULY/46
(or
later
revision(s)
PARTS LIST:
F~EFER
TO BENDU(-KING
SE KT
76A-7,
DATED JULY/96
(or
later
revision(s)
F1GURES/
TABLES:
FIEFERTO BENDIX-MNG
SE
KT
76A-7,
DATED JULY/96
(or
later
revision(s)

THIS
SERVICE BULLETIN IS FAA
APPROVED
FOR
ENGINEERING
DESIGN
SERVICE
BULLETIN
M20-262
ISSUEDATE:
10January,
1997
SUBJECT: TEX~RON LYCOMING
SERVICE BULLETIN
No.
5278,
DATED
8
OCTOBER,
1996,
(OR
SUBSEQUENT
REVISIONS),
RECALL
OF PISTON
PIN,
P/N
LW14077
MODELS/S/N
AFFECTED: ME FOLLOWING
AIRCRAFT SHOULD BE
INSPECTED
TO
DETERMINE
1)
IF
LYCOMING
ENGINE
S/N’s
LISTED
ON
SUBJECT
LYCOMING
SERVICE
BULLETIN,
No. 5278
(OR
SUBSEQUENT
REVISION
ARE
INSTALLED.
2)
IF
CYUNDERASSEMBUES
OM-IICH
INCLUDE
PISTONS
AND PISTON
PINS)
HAVE
BEEN REPIJ\CED
SINCE
15
DECEMBER,
1995
3)
if
PISTON
PINS
ONLY,
HAVE
BEEN
REPLACED
SINCE
15
DECEMBER,
1995
IF
ANY OF
1),
2)
OR
3)
ABOVE
CONDITIONS ARE
FOUND,
COMPLIANCE
WITH
LYCOMING
SERVICE
BULLETIN
No. 5278
(OR
SUBSEQUENT
REVISIONS)
INSTRUC-
TIONS
MUST
BE
ACCOMPLISHED
IN
ACCORDANCE
WITH
ALL PARAMETERS
OF THE
SERVICE
BULLETIN.
M20A,M20B,
M20C,
M20D,
M20E, M20F,
M20G
AL,
SIN’s 8
M20J S/N’s 24-0001
THRU 243380
IF RETROFITTED WITH
NEW,
OVERHAULED
OR
REMANUFACTURED
ENGINES
OR
CYUNDERASSEMBLIES
(PISTONS
8
PISTON
PINS IN
CYLINDERS)
OR
PISTON
FINS
ONLY,
SUPPLIED BY LYCOMING
BET~
15 DECEMBER
1995 THRU
17
SEPTEMBER,
1996.
M20J SIN’s 24-3381
MRU
24-3389,
24-3391
AIRCRAFT
WITH ENGINES
MANUFACT-
URED
BETWEEN
15
DECEMBER,
1995 THRU 17
SEPTEMBER,
1996
INSTALLED DURING
PRODUCTION.
M20M
SIN
27-0001
THRU 27-0210
WITH -AF1B
ENGINE
RETROFIT KIT
INSTALLED
OR
IF
v\nTH
NEW,
OVERHAULED OR
REMANUFACTURED
ENGINES
OR Cn-
INDERASSEMBLIES
(PISTONS
8 PISTON PINS
IN
CYLINDERS)
OR
PISTON PINS
ONLY,
SUPPLIED BY
LYCOMING
BETVMW 15
DECEMBER
1995 THRU 17
SEPTEMBER,
1996.
M20M
SIN 27-0212
MRU
27-0214,
27-0217
NOTE:
Aircraft
Serial
Number
effectivity
is based
on
original
manufactun‘ng
records.
To
determine
final
applicability,
verify engine
sen~al number and
consult
Textron
Lycoming
Service Bulletin
527(8)
or
subsequent
revision
TIME
OF
COMPLIANCE
SEETDCTRON
LYCOMING
SERVICE
BULLETIN No.
5278,
8
OCTOBER,
1996
(OR
LATER
REVISION)
INTF~ODUCTION:
SEETMTRON
LYCOMING SERVICE
BULLETIN
No.
5278,
8
OCTOBER,
1996
(OR
LATER
REVISION)
INSTRUCTIONS:
SEETDCTRON
LYCOMING
SERVICE BULLETIN
No.
5278,
8
OCTOBER,
1996
(OR
LATER
REVISION)
VWRRANTY:
SEETDCTRON
LYCOMING SERVICE BULLETIN No.
5278,
8
OCTOBER
1996
(OR
LATER
REVISION)
REFERENCE
SEE TEXTRON LYCOMING
SERVICE BULLETIN
No.
5278,
8
OCTOBER,
1996
DATA:
(OR
LATER
REVISION)
PARTS
LIST: SEE
TDCTRON LYCOMING
SERVICE
BULLETIN No.
5278,
8
OCTOBER,
1996
(OR
LATER
REVISION)
FIGURESI
TABLES:
SEE TECTRON
LYCOMING
SERVICE
BULLETIN No.
5278,
8
OCTOBER,
1996
(OR
LATER
REVISION)

THIS
SERVICE
BULLET1N
IS
FAA
APPROVED
FOR
ENGINEERING
DESIGN
SERVICE
BULLmN
M20
-263
ISSUE DATE: 15
August,
1997
SUBJECT
Seat
Belt retainer
bushings
nylon
grommet
failure.
MODEYS/N
AFFECTED.
M20
Series
ALL
SIN’s
with Non-lnertial Reel
Shoulder
Restraints installed
M20J
24-0001
thru 24-1685 -With Non-lnertial
Reel
Shoulder
Restraint Assemblies
24r1686
thru
24-TEA
With Rear
Seat Should
er
Restraint
Assemblies
M20K-
25-0001
thru
25-1224
With Non-inertial
Reel
Shoulder
Restraint Assemblies
25-1225 thru 25-TEA Wrth
Rear
Seat
Shoulder
Restraint Assemblies
M20L-
26-0001
thru
26-0041
Wrth
Rear
Seat Shoulder
Restraint Assemblies
M20M
27-0001
thru
27-iBA
\Nnh Rear Seat
Shoulder
Restraint Assemblies
M20R- 29-0001
thru
29-TBA-
With Rear
Seat
Shoulder
Restraint Assemblies
M20J S/N’s 24-1150 thru 24-1417 M20K S/N’s
25-0560 thru 250780
had
Indiana Mills
Seat
8elt and/or Shoulder
Restraint
Assemblies
instail~d
during
production,
however,
if
any
replacement
has been
accomplished,
the
replacement
Seat
Belt/Restraint
Assembly
may
have
the
retainer
bushing,
nylon
grommet
configuration.
NOTE
AM-Safe Brand
shoulder restraint~s
incorporate
a
retainer
bushing
used for the
cargo
restraint
tie
down
system
for
the
rear
seats.
These retainer
bushing’s
should also be
inspected
for
missing
or
defective
nylon
grommets
used
in
the
original
configuration.
TIME
OF
COMPLIANCE:
Within
the
next
25
operational
hours
or
at
next
maintenance action.
INTRODUCTION:
Ramp
inspections
at
some
airports
have
found
the
nylon
grommets
missing
or
broken
from
shoulder hamess
retainer
bushings
on
several model
aircraff. Unauthon’zed
repairs
using
ty-raps
have
been
found. The
Ty-rap’s
locking
tab
may
prevent
the restraint
buckle
from
properly
snapping
into
position
or
may
create
difficuit~s
in
releasing
the
restraint buckle in
an
emergency.
The
intent
of
this
SE
is
to
provide
information for
inspection
and
correctly
repain~ng
any
defective
retainer
bushing grommet
that
may
have
failed.
INSTRUCTIONS:
Figure
SE hi120-263-1
depicts
the
conditions
that
may
be found
on
any
seat
belt/restraint
assembly.
Refer
to
the illustration and
follow
the
procedures
shown
on
the
figure.
VWRRANTY:
Mooney
Aircraft
Corpoiation
will allow
0.5
hours
laborto
inspect
and
repair
the
seat
beltl
harness restraints
on
aircraft still WITHIN
WARRANTY.
The
parts
will
be
available
through
your
Mooney
Service Center.
k~our
account
will
be
credited in
the
normal
manner
when
properly completed
warranty
claims
are
reiumed
to
Service Parts
Department,
Kenviile.
TX.
REFERENCE
FAA General
Aviation Airworthiness
Alerts,
AC No.
43-16,
No,
210,
January,
1996
DATA:
PARTS UST~
Kit Part number
SE M20-263-1
lTEM
P/N
DESCRIPTION
QT/
1 HRSR-1/2
GROMMET
4
Vendor
for
Grommet:
XL
Technologies
1315
So. Park
Dr.
Kernsvitle,
NC
27284
Telephone:
(910)
966-6777
Fax:
(910)
9~6-2887
FIGURES/
TABLES:
See
Figure
SE
M20-263
-1
on
next
page.

t,
~I
;OIC!
5m
rnm
o
I II(
--EXISTING
NYLON
BUSI-IING
IN
PLACE
oo
II
I-_11
(1I\ISPECT
FOR
DEFECTS)
IJNSAFE--NILON
F
BUSIIING
MISSING
co
RETPOFIT
PROCEDUPES
tlRSR-I/P
T~RDMMES
SLIPPED OVER
STUD
c
2.
APPLY
NEAT
FROW
I´•IEAT
GUN Tn
S~-IRINK
GROMMET
o,
i
3
HRSR-1/2
~ROMMET
SWRUNK
IN PLACE
´•\,r,~
´•´•t,\ri´•\,
4
VERIFY
SIIOULDCR
RES7laAINT
SNAPS
OVER
GRUMMET
SECURELY
I III ’Y
\i’
i.
I
i
I(´•´•i
\t\
ii:
1~

THIS
SERVICE BULLETIN
IS
FAA APPROVED
FOR
ENGINEERING
DESIGN
SERVICE
BULLETIN
M20-264
ISSUEDATE:
1
February,
1998
SUBJECT:
Aileron,
Center,
Control
Links
Inspection
MODELSIS~
M20B,
M20C,
M20D,
M20E,
M20F,
M20G ALL
SERIAL NUMBERS
AFFECTED:
M20J
S/N
24-0001 THRU
24-3359
M20K
S/N 25-0001
THRU
25-1999
N120L
ALL SERIAL
NUMBERS
M20M S/N 27-0001
MRU 27-0197
M20R
S/N
29-0001
THRU
29-0042
TIME
wn~in
nex~ 25 hours of
operation
and
in
accordance
wil~
NOTE 2 below.
INTRODUCTION:
There
have
been
reports
of
a
crack
adjacent
to
the
weld
area
of
the
LH
aileron,
center
control
link,
P/N
730005-1.
Since
the
LH
6
RH
are
very
similar,
a
is
requested
that
an
inspection
of
both
of these
control
links be
completed
in
accordance
with
the
instrudions
shown below.
The
part
numbers
to
be
inspected
are
as
follows:
M20B, M20C,M20D,
M20E,
M20F,
M20G,
M20J,
M20K
730005-1
(LH)
6
730006-000
(RH)
M20L,
M20M
730051-501
(LH)
6
730052-501
(RH)
INSTRUCTIONS:
I.
Remove Iower
belly
skin
to
gain
access
to
underside
of
aircraft:
Aluminum
Belly
Skin aircraft lst skin
aff
of
nose
wheel
well
Smooth
fiberglass
belly
aircraft
Forward
fiberglass
skin
NOTEQ
ff
during
a
Visual
inspection
it
is
determined
that
either
control link has
a
reinforcing
gusset
at
the 2nd
900angIe
joint
from
Helm
bearing,
(link
has
been
replaced),
no
further
inspection
is
required
for
that
control link. W both links
have been
replaced,
reassemble
belly
skin
and
proceed
to
step
9
thru 11.
2.
If
a
visual
inspection
determines
that
there
are
no
reinforcing
gussets,
remove
LH
6
RH
aileron,
cen-
ter,
control links. Note location of
spacer
between LH
RH
control links
at
attach
bolt.
Remove
paint
from the
area
to
be
inspected.
3.
When
paint
and/or
any
foreign
maten~al
have
been
removed from
the
weld
area
of
the
2nd
900
angle
joint (2nd
from Helm
bean’ng),
conduct
a
Magnetic
Particle
Inspection
of
each
link
on
that
2nd
90"
angle
joint.
4.
Carefully
inspect
the results
of
the
Magnetic
Particle
Inspection
to
determine if
any
discrepancy
e~a’sts
at
the
weld
area,
either
in the weld
or
in the
adjacent
tube material.
5,
If
no
discrepancies
exist,
dean
area,
prime
and
repaint
area
(epoxy
paint
recommended).
6.
Reinstallthe
e>dsting
good
control
links.
NOTEZ
If
existing good
control
links
are
not
replaced
at
this
time, repetitive
inspections,
in
ac-
cordance with
this
SE,
are
required
at
each
annual
or
100
hour
inspection
thereafter.
7. If
discrepancies
are
found,
proceed
to
PARTS LIST below.
6.
Connect
attaching
bolts,
spacer,
nuts
and washers in
accordance with AC43-13
or
Mooney
Service
3
Maintenance
Manual
instructions.
Lubn’cate
Helm
bearings
withTeffon
spray
lubricant
per
S
M.
9.
Verify
aiieron
rigging
in
accordance
with
the
proper
section
of the
applicable
model’s
S 6
M
manual.
10.
When
rigging
is
verified
to
be
correct,
reinstall
aircraft aluminum
belly
skin
or
fiberglass
skin.