Mooney M20M - Page 219

MOONEY
AIRCRAFT
CORPORATION
M20M
SERVICE
AND
MAINTENANCE
MANUAL
51-00-00
GENERAL
the
rear
spat
on
both
sides.
The
Mooney
M20M
is
an
all
metal,
low
wing
airplane.
The rudder
is
constructed
of
formed aluminum
skins
The
fuselage
cabin
area
is
constructed ofa welded
fastened
to
a
spat
extrusion
at
the
leading
edge
and
4130
chrome-molybdenum
steel tubular
structure.
The
riveted
together
at
the
trailing edge.
steel tubular
structure
is
covered with non-structural A three
piece composite
belly
skin
covers
the
aluminum
skins
fastened
to
the tubular
structure
by
underside
of
the
aircraft
from
the exhaust
cavity
aft
to
rivets,
bolts
and
screws.
the tailcone.
The
tailcone
is
of
semi-monocoque type
construction
The front
seats
are
installed
on
rails
which
are
and
is
fastened to
the
tubular
structure
with
structural attached
to
the floorboard
and
structure
beneath
the
bolts.
Roorboard.
The
wing
is
a
tapered,
laminar
flow,
one
piece
wing.
It The
M20M
has
a
split
type
rear
seat,
using
seat
is
constructed
with
a
one
piece,
full
length
main
spat.
cushions
in
molded
wells
over
the
wing
spats
and
The
spar
is
constructed
from
tapered
cap
strips (7075
individually reclining
rear
seat
backs.
aluminum)
bolted
(huck bolts)
to
webs
(2024
aluminum).
Aluminum
ribs
connect
the
main
spar
to
the
51-10-00
STRUCTURAL
REPAIR
GENERAL
aft stub
spat
and
the
rear
spat.
Extruded
stringers
run
This
section
outlines
structural
repair
procedures
for
the
full
length
of the
wing,
spaced
chordwise for
the
M20M
airplane.
It
is
intended
to
supplement
FAA
strength
and
skin
reinforcement.
The skins
are
stretch
Advisory
AC
43.13-1(
by
showing repair
methods
formed,
wrap
around,
2024-T3
aluminum
ranging
in
specific
to
Mooney
airplanes.
thickness
from
.025
at
the
tip
to
.050
at
the
fuel
tanks.
All structural
repair
must
be:
in
compliance
with
AC
The
completed
wing
assembly
is
mated
to
the
fuselage
43.13-1(
unless
specific Mooneyfactory
repairs
tubular
structure
during
final
assembly
at
the
Mooney
arerecommended,
or
with the
specific approval
of
a
facility.
Removal
of the
wing
from
the
fuselage
Federal
Aviation
Administration
representative
which
is
structure
is
essential
for
most
over
land
type
the
final
authority
in
all
repairs.
This
manual
is
for
transportation.
general
guidance
and has
no
authorized
approval
The
empennage
is
of
similar
construction
to
the
wing.
status.
The
PRODUCT SUPPORT
DEPARTMENT,
A
main
spar spans
the
length
of the stabilizer. Ribs
Mooney
Aircraft
Corporation,
Kenville,
Texas,
should
connect
the main
spar
to
the
stub and
rear
spat.
A
be consulted
for
special
repair
procedures
when
repair
stretch
formed skin
wraps
around
the
leading edge
ribs
of
damaged
structure
is
not
covered
by
published
and
attaches
to
the
rear
spat
on
top
and
bottom.
instructions.
The
elevators
are
constructed
of formed aluminum
skins
fastened
to
a
spat
extrusion
at
the
leading
edge
51-10-01
FASTENER
REPLACEMENT
and
riveted
together
at
the
trailing
edge.
1.
HUCKBOLT
INSTALLATION.
The Huck
Lockbolt
The
vertical
stabilizer
is
constructed
around
a
is
an
interference
fit fastener
used
in
a
rigid
joint
fabricated
main
spar
assembly
with ribs
connecting
the
structure.
A
loose
or
slip
fit Huckbolt
is
unacceptable.
main and
rear
spat.
A stretch
formed,
aluminum skin
The recommended
limits
for Huckbolt
holes
are:
wraps
around the
leading edge
ribs and
is
riveted
to
2LPH-T5
No.
26
(.147
IN.)
No.
20
(.161 IN.)
.161
to .1635
IN.
ALPPH-TG
No.
18
(.1695
IN.)
No.
13
(.185 IN.)
.185
to
.187
IN.
R3001-T6
No.
18
(.1695
IN.)
No.
13
(.185 IN.)
.185
to
.187
IN.
2L426H-T5
No.
26
(.147
IN.)
No.
20
(.161 IN.)
.161
to
.1635
IN.
R3007-T6
3/16
(.187
IN.)
No.
7
(.201
IN.)
.2005
to
.2025
IN
When
the
Huckbolt
is
enlarged
beyond
the
above limits
Aircraft,
Corporation,
Kerrville,
Texas,
for
factory
but
is
straight
and
round,
the
hole
may
be
considered recommendations
when the
preceding
instructions
are
acceptable,
provided
that
the
Huckbolt
cannot
be
inadequate
to
accomplish
the
repair.
pressed
into
the
hole,
with
normal
hand
pressure,
to
a
T,
compensate
for
material
thickness
tolerances,
depth
more
than
50
percent
of the heaviest
material
Huckbolt
length
may
be
increased
by
one
dash
number
being
secured.
Check
enlarged
hole size
at
both ends.
from
the
prescribed length.
When
aFluckboR
pin
of the
Select
Huckbolts
to
fit the oversize
holes.
proper
length
is
not
available,
use a
pin
of
the
next
Oversize
Huckbolt
holes
may
be
repaired
by
replacing
lo"ger length.
2LPH-T5
Huckbolts
with
ALPPH-TG Huckbolts
or
with
NAS
623-2
screws
and
NAS
1021
No.
8
Hex-lock
nuts
(or
equivalent),
provided
the
pitch
distance
is
greater
than
.56
inches
and
the
edge
distance
is
greater
than
.33
inches.
Huckbolts
ALPPH-TG
and R3001-T6
may
be
replaced
with
R3007-T6
Huckbolts
as
necessary.
Consult
the
Product
Support
Department,
Mooney
4-99
51-00-00
OLDWILLWAYNE