manuals.online logo
Brands
  1. Home
  2. •
  3. Brands
  4. •
  5. Mooney
  6. •
  7. Tools
  8. •
  9. Mooney M20M Reference manual

Mooney M20M Reference manual

Other manuals for M20M

2

Other Mooney Tools manuals

Mooney M20S 1998 Installation and user guide

Mooney

Mooney M20S 1998 Installation and user guide

Mooney M20J Owner's manual

Mooney

Mooney M20J Owner's manual

Mooney Mustang M22 1967 Installation and user guide

Mooney

Mooney Mustang M22 1967 Installation and user guide

Mooney Ranger M20C User manual

Mooney

Mooney Ranger M20C User manual

Mooney M20R - Ovation Technical specifications

Mooney

Mooney M20R - Ovation Technical specifications

Popular Tools manuals by other brands

AGI Westfield MKX16 Assembly manual

AGI

AGI Westfield MKX16 Assembly manual

GYS HAND-DUCTION 056923 Translation of the original instructions

GYS

GYS HAND-DUCTION 056923 Translation of the original instructions

Grizzly H7583 instruction manual

Grizzly

Grizzly H7583 instruction manual

Sealey VS0462.V2 instructions

Sealey

Sealey VS0462.V2 instructions

Makita HR2650 instruction manual

Makita

Makita HR2650 instruction manual

Forza 1100H Series manual

Forza

Forza 1100H Series manual

Aventics EBS-PI operating instructions

Aventics

Aventics EBS-PI operating instructions

Martor SECUNORM 175 quick start guide

Martor

Martor SECUNORM 175 quick start guide

jbc N4473 instruction manual

jbc

jbc N4473 instruction manual

FEINMETALL FZWZ-SET-001 quick start guide

FEINMETALL

FEINMETALL FZWZ-SET-001 quick start guide

Worx Professional Sonicrafter WU676 Original instructions

Worx Professional

Worx Professional Sonicrafter WU676 Original instructions

Gage Bilt GB713SH Original instructions

Gage Bilt

Gage Bilt GB713SH Original instructions

Hilti DX 9-ENP Original operating instructions

Hilti

Hilti DX 9-ENP Original operating instructions

norbar NORTRONIC 34399 Operator's manual

norbar

norbar NORTRONIC 34399 Operator's manual

BGS technic 8578 manual

BGS technic

BGS technic 8578 manual

axing BWZ 5-02 Operation instructions

axing

axing BWZ 5-02 Operation instructions

Makita DHR241 instruction manual

Makita

Makita DHR241 instruction manual

Motor Guard JMB-1250 instructions

Motor Guard

Motor Guard JMB-1250 instructions

manuals.online logo
manuals.online logoBrands
  • About & Mission
  • Contact us
  • Privacy Policy
  • Terms and Conditions

Copyright 2025 Manuals.Online. All Rights Reserved.

alrg~
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