/nao-1~7
SVBJECT:
INSTALLATION
OF
OPERATION
PW\CARO
P/N
150010-111
MODELS
EFFECTED:
M20
and
IM22
Series
Aircraft
TIME
OF
COMPLIIINCE:
On
or
before
neX,
100
iiour
Inspection
INTRODIICTION:
P/N
150010-111
is
a
placard
that
is
to
be
adhered
to
an
area
on
the
flight
panel
(ret’erence
shefches
shown
below)
in
full
view
of
the
pilot.
INSTRL[CTIONS:
NOTE
-1.
Sketch
1-
depicts
hlZO
series
flight
panel
2.
Sketch
2
depicts
M22
series
flight
panel
All
placards
are
self-adhering
(pressure
sensitive)
M20
Series
Aircraft
(1)
Location
A
(Shounn
on
Sketch
1)
order
Kit
No.
1
This
is
the
location
far
adhering
placard
150010-111
on
aircraft:
M20C
S/Nls
2121
thru
h?013L
#200
S/N’E
i.
101
thru
2hO
EZ20E
S/M’s
101
to
h80001
E70F
9/N’´•
hi´•0002
thru
h70~85
Placard
F/I
1:00:9-b3
(Gear
Ooum)
is
to
be
adhered
as
sho~a
on
Sketch
1
if
placard
150010-111
is
adhered
per
this
recommended
1A’
location.
(2)
YIILI-V´•II
YI
Y
(Sho~
on
Sketch
1)
Locationl
B
C
Locaiions
B
and
C
(optional)
are
for
other
’120
aircraft
not
feasible
on
location
A.
If
thi´•
placard
cannot
be
installed
on
recommended
locations
A,
R,
or
C,
then
it
is
to
be
adhered
to
;te
left
of
line
A-A
(shorn~
on
Sketch
1)
an
the
flieht
panel--;r
full
view
of
pilot.
(L)
AdilerP
rticker’’
to
outside
of
front
coier
of
?I?O
Series
Aircraft
Oxners
Manual.
M22
Series
iiircraSt
(1)
Adhere
P/I
150010-111
placard
on
M22
S/hi’s
C.70001
and
~70002
as
shorn~
an
Sketch
2.
(2)
Adhere
sticker"
to
outside
of
front
cover
of
~22
Series
Aircraf~
Ouiner;
Manual.
SERVICE
BIILLETIN
KIT
NO.
1
150010-111
Placard
lane)
li0019-h3
Placard
(or,p)
Stic~eri’(ons
SZRTIICE
BlJLLFTIN
KIT
NO.
2
,,,,,,.,,I
it
Sticker
is
made
of
paper
and
has
same
size,
desian,
and
wording
as
P/N
150010-111
placard.
I
oFa
i
~k,
o
09
a
‘B
´•I(´•01*1.):
oh
:-I
onaet
lilt
Il´•Ulrl
ONLI-O´•II´•
I´•UI´•l
M
IN´•
~I´•
II~
I´•
U1
o
hr~un
*lh
rlili´•
L
Ua~
III*
Ihllil~lll´•l´•l´•li´•(
Il´•l´•LI´•lllillb
li´•il´•li´•l.
PJN
150010-111
Plpep~
To
be
Lnsta~led
an
1I1
M-20
esrisa
~ar
locPLLon
’A’
drcralt
in
Lull
vie.
alpllot.
ONI.Y
P/N
150038-45
PLpeard
BYLTCB
1
nm
aERIE8
PLI(IIP~
PANEL)
s
BO
o
6’
O
Q
90~
Q
oPrlnrs
THS
I1RCRl\lr
ONLY-
Oall,~
raaling
awara
manull
8
with
awnsr
manuai
an
bpard
O
8
ear
vau
all
st
v
a
und,l.,nl
all
ol
´•00
P/N
150010--111
Placard
To
be
installed
on
all
M-22
series
aircraft
in
full
view
of
pilot.
SKETCH
2
(M-22
SERIES
FLIGRI~
PANEL)
of
a
SUBJECT:
ALTIMETER
INSPECTION
MODELSPI~EC1TED:
~zoc,
S/N
670001-670135
~20E,
S/N
1177,
1199,
1217,
1268,
1273,
1277,1281,
1283,
1286
thru
1288,
1290,
1292,
1293,
1295
thru
1308,
670001
thru
670062
~20F,
S/N
660001
ihru
660004,
670001
thru
670446
P122,
S/N
670001
and
670002
This
Bulletin
will
also
apply
to
any
other
Mooney
airpla3le
for
which
a
Trleston-Garwin
Model
22-374
aftimeter
was
purchased
between
July
i,
1966
and
August
2,
1967.
~E
OF
COMPLIANCE:
Immedia’;ely,
this
Service
Bulletin
is
mandatory.
INTRODUCTION=
Evidence
has
been
found
that
an
accumulation
of
tolerances
in
some
Weston-Garwin
Model
22-374
altimeters
can
cause
a
malfunction
of
the
instrument.
Since
this
condition
is
li~ely
to
exist
in
all
airplanes
which
are
equipped
with
Model
22-374
altimeters,
this
Service
Bulletin
is
being
issued
to
require
testing
of
the
altimeter
and
replacement,
if
necessary,
on
several
models
of
Mooney
airplanes.
II~STfLUCTIONS:
To
determine
if
the
Weston-Gar~Jin
Model
22-374
altimeters
are
operating
properly,
accomplish
the
following:
1)
Set
barometric
scale
or"
altimeter
to
coincide
with
appropriate
field.
pressure
and
check
altimeter
reading.
It
should
agree
with
field
elevation
allowing
for
a
tolerance
of
plus
or
minus
100
feet.
2)
Set
barometric
scale
of
altimeter
to
29.92
inches
of
hg
(1013.3
mi77;hars)
and
observe
the
altimeter
reading.
3)
Turn
the
bare
mechanism
so
as
to
move
the
scale
to
the
low
end
stop.
During
this
movement,
exert
slight
pressure
forward
and
aft
alternately
in
order
to
see
if
it
is
possible
to
cause
the
internal
mechanism
to
become
disen,oa,Ped.
The
disengagement
will
be
obvious
if
the
pointer
hand
fails
to
rotate
as
the
knob
is
turned.
4)
Turn
the
knob
for
bare
scale
soas
to
move
the
scale
to
the
high
end
stop.
During
this
motion,
again
exert
pressure
by
alternately
pushing
and
pulling
slightly
and
watch
for
needle
slippage.
INSTRUCTIONS:
5)
Turn
the
barometric
scale
back
to
24.42
inches
of
hg
(1013,3
and
compare
this
altimet;er
reading
with
the
reading
obtained
in
Step
2.
The
readings
should
be
the
same.
If
the
pointers
do
not,
at
all
times,
move
in
direct
relation
with
the
bare
scale,
or
if
the
reading
of
Step
2
does
not
agree
with
the
final
reading,
or
if
the
reading
in
Step
1
is
not
within
tolerances,
then
the
altimeter
is
not
working
properly,
and
ii;
should
be
replaced
or
repaired
at
an
approved
facility.
Aircraft
with
defective
altimeters
shall
fly
VFR
only
in
visual
contact
with
the
ground
until
the
altimeter
is
replaced
or
repaired.
The
check
required
by
this
Service
Bulletin
may
be
per-
formed
by
the
pilot.
~ZI´•
OON
R~C;SA
-9
i"
dOX
Zlrz
36
´•1.
SUB;IECT:
Fuel
Filler
Caps
(Shaw
Aero),
Inspection
and
Adjustment
MODUS/
MZ0C
S/N
2623
and
ON,
M20D
S/N
201
gr
ON,
ALL
M20E,
M20F,
M20G,
M20J,
M20K
S/N
AFFECTED:
and
M22
Aircraft
TIME
OF
COMPLIANCE:
Within
next
25
night
hours,
and
every
100
hour/annual
inspection
thereafter.
INTRODUCTION:
Exposure
to
weather.
fuel
fumes,
fuel
and
possibly
other
elements
have
a
deteriorating
effect
on
O’ring
packings
and
seals.
The
two
O’rings
on
the
Shaw
Aero
fuel
filler
cap
assembly
have
been
reported
to
lose
their
resilience
and
sealing
characteristics
after
a
period
oftime
when
exposed
to
these
elements.
This
S.B.
is
intended
to
describe
inspection
procedures
for
this
deterioration.
INSTRUCTIONS:
Fuel
filler
port
cap
assemblies
should
be
checked
periodically
for
proper
sealing
and
should
be
serviced
occasionally
to
prevent
hard
to
open
or
close
conditions.
I
Refer
to
Figure
S.B.
M20-229-1
andthe
following
procedures
for
these
inspections
and
adjustments:
i.
TheO’ring
real
(1)
amur.d
the
cap
assembb
should
be
kept
clean
and
free
of
dirt
orgrit
that
might
cause
abrasive
action
on
seal
or
mating
nange.
Occasional
lubrication
with
petroleum
jelly
or
Tri-Flow
will
keep
the
O’ring
soft
and
pliable.
2.
The
shaft
(2)
running
through
the
center
of
the
cap
housing,
that
actuated
the
rotating
lock
plate
(3)
should
be
lubricated
occasionally
with
Tri-Flow,
or
equivalent,
to
prevent
I
binding
while
opening
or
closing
the
cap
assembly.
This
should
also
lubricate
the
O’ring
;(4)
that
seals
this
shaft.
WARNING
Water
can
enter
the
fuel
tank
through
a
loose
fitting
or
damaged
cap.
This
should
be
corrected
as
soon
as
possible.
3.
The
sealing
capability
of
each
cap
assembly
should
be
checked
periodically.
This
can
be
accomplished
per
the
following
procedures:
A.
Remove
cap
assembly
form
wing
filler
port
and
inspect
O’ring
(1)
for
any
damage
or
brittleness.
Remove
and
replace
if
needed.
B.
Adjust
tension
of
shaft
(2)
and
rotating
lock
plate
(3)
by
removing
cotter
pin
(5)
from
nut
(6)
on
threaded
portion
of
shaft
t2).
Tighten
nut
(6)
so
cap
assembly
handle
(7)
can
be
opened,
turned
and
shut
with
hand
pressure
and
still
provide
the
necessary
seal
of
cap
assembly
to
keep
water
from
entering
fuel
tank.
C.
Fuel
selector
should
be
in
the
OFF
position
prior
to
pressurizing
the
fuel
tanks.
D.
Connect
rubber
hose
to
each
tank’s
vent
line.
Apply
only
one-half
pound
(1/2
psi)
air
pressure.
Check
for
fuel
cap
leaks
by
soaping
circumference
of
ftlIer
cap
assembly
and
observing
bubbles.
Replace
O’rings
if
bubbles
are
observed
and
adjustment
of
the
nut
does
not
stop
the
leak.
’’CAUTION"
Use
only
one-half
pou
nd
(0.5
psi)
of
air
pressure
in
tank.
Higher
pressure
ma~
damage
the
fuel
tank.
"NOTE"
MZOI<
aircraft
must
have
the
anti-siphon
valve
inside
filler
port
propped
open
during
this
pressure
testing.
REFERENCE
DATA:
N/A
PARTS
LIST:
(Parts
NOT
included
in
kit
order
if
needed).
Part
Number
Description
Qty.
Required
MS29513-010
O’Ring
tcenter)
1
MS29513-338
O’Ring
touter)
(for
431-9R
and
1
531-001
cap)
Page
2
of
2
SE.
M20-229A
2-12-86
FIGURES/TABLES:
I’
I
FIGURE
S.B.
M20-229-1
g
b;L
MOONEY
L\1RCRAFt?i~OR
NLIMBER
-r-
-´•r
r
bdX
rj‘´•
KERRYILLE,
rrXAS
76026
g
i-i;i´•;;
.":rtnSeuLLETIN
IS
FA*
APPROVED~
;-i
.-_-I-
SUBJECT:
Inspection
of
Fuel
Tank
Sealant
Application
MODELS/
M20B,
M20C,
M20D,
M20E,
M20F,
M20G
M22
ALL
SERIAL
NUMBERS.
S/N
AFFECTED:
M20J:
thru
24-1498;
M20K:
SM25-0001
thru
25-0854.
h120J:
S/N23-1499
ON
and
M20K:
S~25-0855
ON
ONLY
IF
FUEL
TANK
HAS
BEEN
RESEALED
BY
FIELD
PERSONNEL.
TIME
OF
COMPLIANCE:
Within
next
50
flight
hours
or
at
next
scheduled
inspection.
INTRODUCTION:
Reports
have
been
received
that
fuel
and
water
have
been
found
trapped
between
ribs
due
to
one
d~more
rib
drain
holes
being
sealed
over
during
tank
sealing;
particularly
in
tanks
that
have
been
resealed.
INSTRUCTIONS:
General
Inspect
to
ensure
all
required
rib
holes
are
open
to
allow
fuel
(or
any
water)
to
move
to
the
lowest
area
of
the
tank.
Refer
to
Figures
M20-230-1
thru
-7
for
areas
to
check
for
specified
holes
to
be
open
and
NOT
filled
with
sealant
compound.
i.
Position
airplanes
in
an
approximate
level
attitude
tall
axis)
on
its
landing
gear.
Drain
fuel
per
instructions
in
applicable
Service
and
Maintenance
Manual.
2.
Carefully
remove
fuel
tank
access
covers
on
top
ofwing
as
indicated
below
for
a
particular
model
(reference
Figure
MZO-uO-l).
NOTE
In
lieu
of
access
cover
removal
optional
methods
of
inspection
are
acceptable.
f
However,
the
method
MUST
be
demonstrated
to
the
local
FAA
inspector
that
a
poshi~e
determination
can
be
made
that
all
holes
are
open
and
the
intent
of
this
Service
Bulletin
has
been
complied
with.
A.
MZOB,
M20C.
MZOD.
MZOE
and
MZOG
Models:
Access
Cover
No.O
required.
Fuel
Transmitter
O
optional.
B.
AIZOF
and
hIZOJ
Models:
Access
Cover
NoOrequ~red,
NoO~plional.
C.
MZO~
Xlodel:
Access
Cover
No~nd
O
required.
No.
O
8(
O
optional
D
h122
h~lodel:
Access
Cover
No.O
andO
required,
NaO.
06rOoplional.
3.
Inspect
each
tank
bay
outboard
of
each
rib
station
for
trapped
fuel
(or
an~
liquid)
that
has
not
drained
through
the
passage
holes
at
each
rib
station
to
the
fuel
tank
sump
drain
area.
4.
Inspect
each
rib
station
(refer
to
Figure
M20-230-2
thro
-7)
to
determine
that
all
fuel
passage
holes
are
open
to
allow
fuel
to
drain
from
outboard
of
rib
stations
to
the
fuel
tank
sump
area.
5.
There
should
be
no
fuel
(or
any
liquid)
trapped
outboard
of
any
rib
station.
If
a
positive
determination
cannot
be
made
that
fuel
is
not
trapped
and/or
that
all
holes
are
open,
the
access
covers
marked
"Opticlnal"
in
paragraph
2.
A
thru
D
above,
should
be
removed
to
complete
the
inspection.
6.
Ifinspcction
determines
all
holes
are
OPEN
in
the
appropriate
ribs
as
shown
in
figures
M20-230-2
thru
-7
this
portion
of
inspection
is
completed.
Proceed
to
Step
8.
i
7.
Ifinspcction
dctersines
311
holes
are
NOT
DPEN
in
Ihe
apprapriale
ribs
as
shou~n
in
Figure
M20-230-2
thru
-7
proceed
as
follows:
A.
Determine
csact
position
of
rib
holc)s)
that
are
sealed
over.
B.
U\ing
pointed
csacto
knife
clear
hole
of
sealant;
be
careful
not
to
cut
sealant
from
rib
flangc.
S.B.
M20-230A
.Date:
1-16-86
Page
2
of
7
C.
if
after
clearing
hole
it
appears
that
fuel
can
get
under
adjoining
sealant
carefully
i’
carefully
reseal
area
without
covering
hole.
use
PRI422BM
or
B2
sealant.
D.
Proceed
to
Step
8
8.
INtall
all
removed
access
covers
per
Service
and
Maintenance
Manual
and
Figure
M-20-230-8.
I
Use
PR1403-G-B2
or
equivalent
sealant
as
specified
in
S
gr
M
Manual,
noting
cure
time
(PR14UB-1/2
or
B-2
may
be
used
if
necessary)
"CAUTION"
Use
of
AN507
screffs
longer
than
7/16
inch
will
puncture
acorn
anchor
nut
in
access
plate.
REFEHENCE
DATA:
N/A
PARTS
LIST:
NIA
FIGURES/TABLES:
See
Figure
M20-UO-1
thru
M20-230-7.
C
f"
Seal
afl
stringer
9E
rib
flungcs,
top
and
bottom
of
tank
FUEL’I’I1N‘K
RIBS
AFFECTED
r~n
M20F
M20K
m20J
hll
nircrnlt
M22
M22
M20K
M22
Witlg
Lcnditlg
Edge
f~-t
r---rll-r~r´•
tl´•ti~
ti
tjsj?zirrr*r
Trulk
Vent
Assy
t;
I,
I,
oQo
O
2
:t
it
(I
:ti
I*
i:
cc*
S~t
Ti:)’f=C,1
s,?l
,I´•
t,c,
t~;
c
´•tl
r-
’F
i~Lli
j
,I
´•r´•
i+~
tl
ci
I
ii-
I’
I;
rl
,L
*b
Lbl-.-"-:Y_
I
it
c
.´•,-----,.~,.,..er.’."
-f~
t:’
5
,c,
c
.i:
i,,
l’i
tl,t
It.
I
,I
I!
i
?l
:C:
;1
,i
;t,
i
5’
-1-
--r
Ci
b
C~
´•I
ft\
t´•
c.~
´•c*
c
-*-t
-L
L
C
C*
C
I
B~D
Tank
W.S.
W
W.S.
W,S.
w.s.
w.5.
w.s.
Drain
24.50
103.5
88.75
74.00
59.25 43.50
Fuel
filler
Qty.
gauge
o\o
port
location
optional
on
3,
will
vary
this
with
a/e
BCCBSS
Drain
holes
thru
stringers
on
models
cover
bottom
side
of
wing
to
be
open.
(4PLCS)
FIGURE
M20-230-1
IVIIIW
I
nnKlhlC.
n~Whl
DRnM
TnT,
~C
Wl~r.\
Seal
rib
as
shown
(this
side
only),
’i
Seal
all
rivets,
nut
plates
St
natljies
(ALL
MODEtS).
´•t´•
i
"i:
111
\\t´•
Seal
bath
side
Seel
both
sides
´•r;iF;´•
:i
of
rib
-1-
Top
Wing
Witlg
Top
of
rib
c~
-t´•
-I-
-t
i
-t-
\t-
3
´•-t’
jI__~__
1
r,
i-
-~-11751
t
r´•´•´•-;´•_-1-_
-t-
~nti-slosll
valves
(h120K)
(2
ca.)
I~
G
vent
holes
thru
L’
rib
to
remain
open
after
sealing.
Ileopcn
aftcP
(alI
models)
-1-
scaling
1
Iiole
(M?OK)
8
holes
(All
i\
´•t-
oLlicr
aircraft)
1.’,
de
Fuel
pickup
I::
strainer
r.
&linger
s~
td
rn
W,S.
43.50
Inboard
fuel
qty.
transmitter
attach
aoint
7Tr,
o\
W,S.
24.50
FIGURE.
M20-230-3
FIGURE
M20-230-2
fl
Willg
’I.op
JI!
Wing
Top
1
-1-
:-1-
,Il!´•i;:
´•1´•
1
i
I~
----r*-
I
O
Seal
both
sitlcs
of
rib
B
´•:i.
´•i´•
(M20K
St
M2)
(All
uroutld)
i’i-
´•-i-
Scalthi~
side
only
~’M2oF.
M201)
Seal
all
rivets,
flenges
i´•’
C
Ilolcs.
t
-C
´•´•1-´•~
tf-
’Scnl
both
sides
of
rib
as
showtl,
~31
t
t-’
-I-
12
holes
thru
rib
It~-";
j.
to
rcmnin
open
-h
I´•’
fl
(M20F,
M20J,
M20K,
M22)
---´•t~
1-
7
Ides
thru
rib
E.
/L
to
rernain
open
1-
Vent
(7
plcs)
i
Reopen
nftcr
holes
holes
Vent
‘´•-\’"20"
6;M22)
seali~!g
(3
ptcs)
~1
(M20F.
M20J,
M201(
~!f
/’Reopen
after
;I
6i
M22).i
sealing
(M20K
St
M22)
j
IIl’-r-------
-1:
11
j
r--~l-i--iiii.
NOTE:
This
is
a
tank
t;-
w.s.
74.90~-
W.S.
59.25
close
out
rib
on
M20B,
M20C,
M20D,
M20E
M20G
and
should
be
sealed
on
inboard
side
only,
Seal
FIGUKE
M20-230-4
all
rivets,
flanges
holes,
FIGURE
M20-230-5
09
I~
td
Vetlt
holes
3
-CI
n
(8
plcs)
Close
out
rib
otl
M20K-
Seal
-c+
inboard
side
´•I~-I
c
otlly,
Seal
all
´•1-
f
i
rivets,
flnngcs
cSt
holes.
15
holes
to
be
reopened
~II
Scnl
inboard
rtftcr
se:lling
side
only
1:
(M22
otlly)
seal
all
rivets,
nnngcs
J~
holes.
i
Witll:
;i;
Top
Wing
Too
W.S.
103-5
(M22
Only)
(M22
Only)
FIGURE
M20-230-7
o\
FIGURE
M20-230-6
"F
~7
r‘
Faysurface
seal
nnnge
Wing
Top
Stlrface
wet
install
screws
on
nll
access
covers
Do
not
use
screws
longer
than
7/16"
I
ii
´•’J~
i
i
i
Seal
inside
surface
of
all
access
covers
sealing
all
rivets
View
looking
up
nutplates
as
shown
from
inside
tank
(REF.
S
M
Manual)
~tlvl
FIGURE
M20-230-8
THIS
SERVICE
BULLETIN
IS
FAAAPPROMD
FOR
ENGINEERING
DESIGN
SERVICE
BULLETIN
M20-ZB1
ISSVEDATE:
1
December.
1996
SUBJECT:
BENDIXKIND
SERVICE
BULLETIN
No.
SE
KT
7BA-7,
JULY/96
(or
later
revision(s)),
KT
76A
ATC
TRANSPONDER.
MODELSISIN
AFFECTED:
ALL
MODELS
OF
MOONEY
AIRCRAFT
MANUFACTURED
SINCE
1975
(INCLUDES
M20C,
MME.
M20F,
MZOJ,
M20K
MZOC
M2OM,
AND
M20FO
AND
ANY
MODEL
MAT
MAY
HAM
HAD
A
KT
7BA
TRANSPONDER
RETROFITTED
SINCE
1875
(INCLUDES
MZO,
M20A.
M20B,
M20D,
M20G,
OR
M22)
(APPLIES
TO
ALL
S/N’s)
TIME
OF
COMPLIANCE:
REFER
TO
BENDIXKING
SE
KT
70A-7.
DATED
JULY/SE
(or
later
revision(s)
INTRODUCTION:
1.
Bendix-King
SeNice
Bulletin
No.
KT
70A-7
provides
information
that
indicates
the
integrated
cir-
cult
(IC)
of
the
KT
78A,
P/N
0Bg1082-00/1~02,
SIN’s
from
83,000
to
109,000,
may
possess,
or
progress
to.
an
electronic
breakdown
within
the
IC
that
causes
either
or
both
of
the
following
malfunctions:
1)
The
unit
may
incorrectly
interpret
the
output
of
the
encoding
altimeter.
or
2)
7he
unit
may
transmit
a
code
other
than
what
is
set
land
shown)
on
the
face
of
the
transponderunl
2.
The
subject
Bendix-King
SE
pro\i~es
the
compliance,
relrofl,
warranty
and
parts
list
information
necessary
for
the
relront
procedures
to
be
accomplished
by
apprapiiately
rated
Bendlx-King
Serv
ice
Centers.
Service
INSTRUCTIONS:
REFER
TO
BENDIX-KINO
SE
KT
78A-7.
DATED
JULYlSE
tar
later
revision(s)
VII~RRANPI:
REFER
TO
BENDIX-KINO
58
KT
7BA-7.
DATED
JULY/SE
(or
later
revision(s)
REFERENCE
DATA:
REFER
TO
BENDIX-KINO
SE
KT
7BA-7.
DATED
JULYISE
(or
later
revision(s)
PARTS
LIST:
REFER
TO
BENDIX-KING
SE
KT
7BA-7,
DATED
JULY/96
(or
later
revision(s)
FIGURES/
TABLES.
REFER
TO
BENDIX-KINO
58
KT
7BA-7.
DATED
JULYIS6
(or
later
revision(s)
MOONEY
"-~i"
SERVICE
INSTRUCJlOr\l
S.I.
No.
M20-40
Date:
12-2-76
SERVICE
INSTRUCTION
SUBJECT:
BAGGAGE
COMPARTMENT
TIE
DOWN
STRAP
ASSEMBLY
REPLACEMENT
MODE
LS
AFFECTED:
Model
Serial
Effectivity
M20F
680001
thru
22-1362,
22-1364,
22-1365,
22-1367,
22-1368,
22-1369,
22-1371
thru
22-1376,
22-1378
thru
22-1381,
22-1385,
22-1386,
22-1388
thru
22-1394,
22-1396,
22-1399
thru
22-1407
~1120E
680001
thru
21-1180
M20C
680001
thru
20-1196,
20-1198,
20-1199,
20-1202,
20-1204
and
20-1205
M20G
680001
thru
700006
M22
680001
thru
700006
TIME
OF
COMPLIANCE:
At
next
scheduled
inspection
or
sooner
at
owner’s
discretion.
INTRODUC
TION:
On
the
aircraft
noted
above
the
material
used
for
the
baggage
compartment
tie
down
rings
was
found
to
be
of
an
incorrect
type.
Therefore,
it
is
recommended
that
the
entire
tie
down
strap
assemblies
be
replaced.
INSTRUCTIONS:
Remove
existing
baggage
compartment
tie
down
strap
assemblies
and
replace
with
the
new
assemblies
called
for
by
the
parts
list.
SERVICE
INSTRUCTION
Qty.
Part
No.
Part
Name
ICIT
S.I-
M20-40-1:
2
010003-505
Baggage
Strap
Assy
2
010003-507
Baggage
Strap
Rssy
S.I.
M20-40
Compliance
Card
COMPIJANCE:
Make
Log
Bogk
entry,
fill
out
and
return
Compliance
Care
MOONEY
SERVICE
INSTRUCTION
NUMBER:
S.I.
M20-62
DATE:
10-13-82
SUBJECT:
REPLACEMENT
of
COLERERSEE,
STARTER
SOLENOID
7iIH
CUTLER-HAMMER,
P/N
6041H105A
MODELS
Mooney
Model
M20g
S/N
25-0681
thru
25-0719
and
any
M20
series
aircraft
that
have
had
a
Cole-Hersee
solenoid
installed
in
plan
of
the
original
PrestoLite.
TIME
OF
COMPLIANCE:
At
the
nut
scheduled
maintenance
or
sooner
at
owners
discretion.
INTRODUCIlON:
There
have
beenreports
of
the
contacts
sticlring
closed
on
CoIe-Hersee
starter
solenoids
on
Mooney
M20g
airplmes.
This
causes
power
transmission
to
the_starter
when
the
master
switch
is
turned
on.
The
propeller
will
rotate
bat
the
engine
will
not
start
if
magneto
switch
is
off.
It
is
recommended
that
the
Cole-Hefiee
solenoid
be
replaced
with
the
improved
solenoid.
INSTRUCTIONS:
iC*UllIlNl
CAUTION
Exetcise
ertreme
caution
in
the
area
of
the
propeller
when
energizing
the
electrical
system.
a)
Pull
AUX.
BUS
and
IGN-TACR,
CIG
LTR
circuit
brea~ers,
or
disconnect
battery.
b)
Disconnect
electrical
wiring
from
the
fear
(4)
terminals
of
the
Coie-Hersee
solenoid.
The
solenoid
is
located
on
the
coc~lpit
side
of
firewalI
forrvard
of
the
co-pilot
seat
on
M20g
and
h1205.
Earlier
model
aircraft
have
solenoid
located
on
engine
side
of
~ewaI1,
ontboard
side
of
pilots
footwell.
c)
Remove
solenoid
from
the
firewalIby
unscrewing
(2)
AN3-3A
bolts
or
MS35206-263
screws
from
nut
plates.
d)
Retain
ground
wire
(21PS10~8)
to
use
with
new
solenoid.
e)
Drill
oat
rivets
attaching
upper
nut
plate,
see
drawing
940020,
and
remove
nut
plate.
Clean
up
bum
and
debris.
a
Enlarge
rivet
hole
per
drawing
940020
for
mounting
new
solenoid.
h)
Plug
the
lower
told)
mounting
hole
with
AN3-3A
bolt
and
AN960-10
washer
per
drawing
no.
940020.
i)
Secure
solenoid,
P/N
6041H105A,
with
(2)
AN3-3A
bolts,
(1)
AN970-4
washer,
(4)
AN960-10
washer
and
(2)
AN365-1032
nuts
in
the
new
location
pet
drawing
no.
940020.
NOTE:
man
ground
wire,
21PS10A18,
under
bolt
head
per
940020
drawing.
j)
Seal
any
holes
or
openings
in
firewall
with
Proseal
700
sealant
per
drawing
940020.
L)
Ream
holes
in
wire
terminals
to
acwpt
3/8"
posts
on
solenoid.
1)
Connect
the
electrical
wires
to
terminal
posts
on
new
solenoid
per
drawing
940020.
Relative
position
of
wires
will
change
very
little
from
replacement
of
the
old
solenoid
with
the
new
solenoid.
m)
Verify
that
no
interference
is
present
between
new
wiring
location
and
any
other
components
or
structure.
n)
Chac~
system
for
normal
operation
and
return
aircraft
to
service.
O)
Enter
compliance
note
into
log
boot
REFERENCE
DATA..
Drawing
940020,
Cutler-IIammer
Solenoid
Retrofit
PARTS
I;IST:
Order
940020-501
git.
FIGURE/TABLES:
See
Drawing
940020.
NIOONEY
SERVICE
INSTRUCTIO
Page
1
SI
M20-70
DATE:
1-1-84
SUBJECT:
FUEL
IDENTIFICATION
DECAL.
MODEL/SERIAL
NUMBERS
AFFECTED:
Mooney
Aircraft,
all
models.
NOTE:
M20g
25-0613
and
on,
M20J
24-1327
and
on
aircraft
have
these
decals
factory
installed.
TIME
OF
COMPLIANCE:
At
owners
earliest
convenience.
INTRODUCTION:
Mooney
M20
Series
aircraft
have
a
decal
applied
to
each
fuel
filler
cap
to
indentify
the
type
and
quantity
of
fuel
as
required
by
regulation
for
the
proper
operation
of
the
engine
installed
in
the
aircraft.
To
further
identify
the
proper
type
of
fuel
required
in
aircraft
the
General
Aviation
Manufacturers
Association
(GAMA),
in
a
joint
effort
with
its
members,
has
developed
a
color-coded
decai
that
can
be
placed
adjacent
to
the
fuel
filler
openings
on
all
aircraft.
The
purpose
of
this
decal
is
to
aid
ground
personnel
in
selecting
the
proper
fuel
when
refueling
the
aircraft.
There
have
been
instances
of
the
wrong
type
of
fuel
used
to
refuel
some
piston
engine
aircrafts.
INSTRUCTIONS:
To
obtain
and
apply
the
decals
for
your
Mooney
the
following
procedures
should
be
followed.
i.
Show
aircraft
model
and
serial
number
on
the
order
form
to
your
Mooney
Marketing
or
Service
Center.
Decals
are
1.00
each
(net).
2.
When
the
decals
are
received
select
the
desired
location
to
apply
the
decals.
(A
recommended
location
is
as
shown
in
Figure
1.)
This
should
be
so
the
ground
servicing
personnel
can
read
the
decal
while
removing
the
fuel
cap
and
filling
the
fuel
tank,
(normally
from
the
leading
edge
side
of
the
wing).
3.
Clean
the
area
selected
with
a
solution
of
water
and
mild
aircraft
detergent.
Rinse
thoroughly
with
clean
water
and
dry
with
a
clean
cloth.
4.
Peel
backing
paper
from
decal
and
apply
smoothly.
Work
out
all
bubbies
during
application.
Be
sure
the
edges
of
the
decal
are
securely
stuck
to
aircraft
surface.
Peel
cover
mask
from
face
of
decal.
5.
Follow
the
same
procedure
for
selected
locations
adjacent
to
all
fuel
tank
filler
openings.
6.
Release
aircraft
to
service.
REFERENCE
DATA:NIA
PARTS
I;IST:
QTY
PART
NO.
DESCRlPTION
2
150080-167
Decal,
Gas
Grade
AVGAS
ONLY
FIGURES/TABLES:
Figure
1.
s~’
GRADE
GRADE
IoOLL
100
AFT
4.0
in.APPX.
CO/BD
FUEL
FILLER
CAP.
VIEW
LOOKING
DOWN
LEFT
WING
F1GURE
1
lanooNEv
~p
SERVICE
INSTRUCTION
Page
1
S.r.
M20-73
4-24-85
SUBJECT:
Mooney
Aircraft
Fuel
Tank
Repair
by
Field
Personnel
MODELS/
S/N
AFFECTED:
M20B,
M20C,
M20D,
M20E,
M20F,
~v120G.
M20J,
M20K
and
M22,
All
Serial
Numbers
TIME
OF
COMPLIANCE:
At
every
fuel
tank
resealing
maintenance
or
repair.
INTRODUCTION:
Reports
havebeen
received
that
fuel
and
water
have
been
found
trapped
between
ribs
due
to
one
or
more
rib
drain
holes
sealed
over
during
resealing
procedures.
Service
Bulletin
M20-230
has
been
prepared
for
a
one-time
inspection
of
fuel
tanks.
The
intent
of
this
S.I.
is
to
assure
that
all
fuel
tanks
resealed
by
field
personnel
subsequent
to
the
one-time
inspection
is
done
in
accordance
with
S.B.
M20-UO
and
current
Mooney
procedures.
INSTRUCTIONS:
Refer
to
the
appropriate
section
of
your
Mooney
Service
and
Maintenance
manual,
and
to
Mooney
Service
Bulletin
S.B.
M20-230
land
subsequent
revisions)
when
any
fuel
tank
reseding
is
to
be
accomplished
on
any
of
the
above
listed
Mooney
aircraft
models.
Particular
attention
should
be
shown
to
assure
that
all
holes
required
for
fuel
movement
between
fuel
bays
are
open
and
clear
of
sealant.
REFERENCE
I)ATAr
(1)
Mooney
Service
Bulletin
M20-230
land
subsequent
revisions)
(2)
Mooney
Service
Maintenance
Manual
(applicable
to
speciftc
aircraft
model
being
repaired).
TARTS
LISTr
N/A
FIGURE/
TABLE:
N/A
C
MOONEY
SERVICE
INSTRUCTION
DATE:
1-15-92
SUBJECT:
REPLACEMENT
OF
TORSION
SPRING
IN
DRIVE
CLUTCH
ASSEMBLY
OF
GEC
(PLESSCI)
LANDING
GEAR
ACTUATORS,
MOONN
P/N
880037-505
AND
880037-507.
SEE
GEC
(UK)
AEROSPACE
INC.,
SERVICE
INSTRUCTION
No.
SI-ll,
DATED
12/17/91
or
SUBSEQUENT
REVISION.
MODELS/
S/N’S
MOONEY
M20J,
S/N
24-0001
THRU
24-TEA
(WTTH
GEC
[PLESSC~
ACTUATOR
INSTALLED)
AFFECTED:
MOONN
M20K.
S/N
25-0001
THRU
25-TEA
(WITH
GEC[PLESSEY]
ACTUATOR
INSTALLED)
MOONEY
M20M,
S/N
27-0001
THRU
27-TEA
(WTTH
GEC
[PLESSC/I
ACTUATOR
INSTALLED)
MOONN
M20L,
S/N
26-0001
THRU
26-TEA
(WITH
GEC
[PLESSC~
ACTUATOR
INSTALLED)
AND
AL,
M20
SERIES
AIRCRAFT
RETROFITTED
WITH
SUBJECT
ACTUATORS.
TIME
OF
COMPLIANCE
AT
1000
FLIGHT
HOURS
OR
SCHEDULED
MAINTENANCE
JUST
PRIOR
TO
REACHING
1,000
FLIGHT
HOURS.
INTRODUCTION:
There
have
been
2
reports
of
a
malfunction
of
the
torsion
spring
at
1200
and
1500
Right
hours
in
GEC
(Plessey)
Model
No.
R5329M12-1
or
R5329M24-1
(Mooney
P/N
880037-505
and
-507)
landing
gear
actuators
dun’ng
operation
in
Mooney
aircraft.
This
Mooney
SeM’ce
Instruction
is
to
notify
field
maintenance
personnel
of
the
GEC
(UK)
Service
Instruction,
No
S:-ll,
dated
12-17-91
which
requires
torsion
spring
replacement
at
1,000
Right
hours.
INSTRUCTIONS:REFERENCE
SEE
GEC
SERVICE
INSTRUCTION
S1-ll,
DATED
12/17/91
or
SUBSEQUENT
REVISION.
DATA:
SEE
GEC
SERVICE
INSTRUCT(ON
SI-ll,
DATED
12/17/91
or
SUBSEQUENT
REVISION.
PARTS
LIST:
SEE
GEC
SERVICE
INSTRUCTION
SI-Il,
DATED
12/17/91
or
SUBSEQUENT
REVISION.
FI
GURESI
TABLES:
SEE
GEC
SERVICE
INSTRUCTlOl\i
S1-ll,
DATED
12/17/91
or
SUBSEQUENT
REVISION.
GEC
SeM’ce
Instruction
Sf-ll
and
spring
replacement
kit
am
available
from
GEC
(UK)
Aerospace
Inc.,
110
Algonquin
Parkway,
Whippany,
NJ
07981-1640,
Telephone
(201)
428-9898,
FAX
(201)
884-2277,
Product
Support
Direct
Telephone,
(201)
428-8787
85-24-03
MOONEY
AIRCRA~r
CORPORATION:
Amendment
39-5173.
Applies
to
Models
M20B,
M20C,
M20D,
M20E,
M20F,
M20G,
M20J,
M20K,
and
M22
tall
Sen’al
Numbers
(S/N~
airplanes
certificated
in
any
category.
Compliance:
Within
100
hours
time-in-service
after
the
effective
date
of
this
AD
or
at
the
next
annual
inspection,
whichever
occurs
first,
unless
already
accomplished.
To
preclude
fuel
contarnination
and
water
entrapment
in
the
fuel
tanks
accomplish
the
foElo\nring:
(a)
For
Models
M20B,
M20C,
M20D,~
M20E,
M20F,
M20G
tall
S/N),
M20J
(S/N
24-0001
through
24-1498),
M20K(S/N
25-0001
through
25-0854)
and
M22
tall
S/N)
airplanes,
visually
inspect
all
fuel
tank
bays
and
rib
stations
in
accordance
with
the
instructions
contained
in
Mooney
S/B
M20-230,
dated
Apn’l
10,
1985.
Repair
all
discrepancies
found
prior
to
further
flight.
(b)
For
Models
M20C
(S/N
2623
through
20-1258),
M20D
(S/N
201
through
260),
M20E,
M20F,
M20G,
M20J,
M20K
and
M22
tall
S/N)
airplanes,
visually
inspect
the
fuel
tank
filler
cap
assemblies
in
accordance
with
the
instructions
contained
in
Mooney
S/B
M20-229,
dated
Apn’l
10,
1985.
Repair
all
discrepancies
found
prior
to
further
flight.
(c)
For
Models
M20J
(S/N
24-1499
and
on)
and
20K
(S/N
20-0855
and
on)
airplanes
that
have
had
any
fuel
tank
reseaied
after
initial
installation
at
the
factory,
visually
inspect
all
fuel
tank
bays
and
db
stations
in
accordance
with
the
instructions
contained
in
Mooney
S/B
M20-230
dated
April
10,
1985.
Repair
all
discrepancies
found
prior
to
further
flight.
(d)
Airplanes
may
be
flown
in
accordance
with
FAR
21.1
97
to
a
location
where
this
AD
may
be
accomplished.
(e)
An
equivalent
method
of
compliance
with
this
AD,
if
used,
must
be
approved
by
the
Manager,
Airplane
Certification
Branch,
ASW-150,
Federal
Aviation
Administration,
Southwest
Region,
Post
Offi~
Box
1689,
Fort
Worth,
Texas
76101.
All
persons
affected
by
this
directive
may
obtain
copies
of
the
documents
referred
to
herein
upon
request
to
Mooney
Aircraft
Corporation,
Post
Office
Box
72,
Kenville,
Texas
78028-0072
or
FAA,
Office
of
Regional
Counsel,
Room
1558,
601
East
12th
Street,
Kansas
City,
Missouri
64106.
This
amendment
becomes
effective
on
January
6,
1986.
CaRPORA
nON
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