# Textron Aviation Multi-Engine Service Bulletin MEB-57-02: No revision named

- Rights: © Textron Aviation Inc. Filed by the FAA in regulations.gov docket FAA-2018-0068, the docket of AD 2018-03-03, 2018-03-03 R1. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Textron Aviation Multi-Engine Service Bulletin MEB-57-02](https://openairdocs.org/service-documents/cessna/meb57-02.md)
- Title as filed: meb-57-02
- Pages: 10
- PDF: https://openairdocs.org/files/sha256/8a/48/8a48fc60d79ce1aeb29335e196102a14d0a620924bb47b736b27872511315c4c
- Page: https://openairdocs.org/service-documents/cessna/meb57-02/file/8a48fc60d79c

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Multi
-
engine
SER
VICE
BULLETIN
MEB
-
57
-
02
TITLE
WINGS
-
ACCESS
P
ANEL
INST
ALLA
TION
FOR
FOR
W
ARD
SP
AR
EFFECTIVITY
MODEL
SERIAL
NUMBERS
402C
402C0001
thru
402C1020
414A
414A0001
thru
414A1212
421C
421C0001
thru
421C1807
REASON
Customers
have
requested
an
access
panel
to
gain
easy
access
to
the
forward
spar
for
inspections.
DESCRIPTION
This
service
document
provides
parts
and
instructions
to
trim
the
lower
skin
and
install
an
access
panel
on
the
wings.
COMPLIANCE
OPTIONAL.
This
service
document
can
be
accomplished
at
the
discretion
of
the
owner
.
A
service
document
published
by
T
extron
A
viation
may
be
recorded
as
completed
in
an
aircraft
log
only
when
the
following
requirements
are
satisfied:
1)
The
mechanic
must
complete
all
of
the
instructions
in
the
service
document
,
including
the
intent
therein.
2)
The
mechanic
must
correctly
use
and
install
all
applicable
parts
supplied
with
the
service
document
kit.
Only
with
written
authorization
from
T
extron
A
viation
can
substitute
parts
or
rebuilt
parts
be
used
to
replace
new
parts.
3)
The
mechanic
or
airplane
owner
must
use
the
technical
data
in
the
service
document
only
as
approved
and
published.
4)
The
mechanic
or
airplane
owner
must
apply
the
information
in
the
service
document
only
to
aircraft
serial
numbers
identified
in
the
Effectivity
section
of
the
document.
5)
The
mechanic
or
airplane
owner
must
use
maintenance
practices
that
are
identified
as
acceptable
standard
practices
in
the
aviation
industry
and
governmental
regulations.
No
individual
or
corporate
organization
other
than
T
extron
A
viation
is
authorized
to
make
or
apply
any
changes
to
a
T
extron
A
viation
-
issued
service
document
or
flight
manual
supplement
without
prior
written
consent
from
T
extron
A
viation.
T
extron
A
viation
is
not
responsible
for
the
quality
of
maintenance
performed
to
comply
with
this
document
,
unless
the
maintenance
is
accomplished
at
a
T
extron
A
viation
-
owned
Service
Center
.
APPROV
AL
T
extron
A
viation
received
F
AA
approval
for
the
technical
data
in
this
publication
that
changes
the
airplane
type
design.
FLIGHT
CREW
OPERA
TIONS
No
Changes
MEB
-
57
-
02
December
20
,
2017
Page
1
of
8
T
extron
A
viation
Customer
Service
,
P
.O.
Box
7706
,
Wichita
,
KS
67277
,
U.S.A.
1
-
316
-
517
-
5800
This
document
contains
technical
data
and
is
subject
to
U.S.
export
regulations.
This
information
has
been
exported
from
the
United
States
in
accordance
with
export
administration
regulations.
Diversion
contrary
to
U.S.
law
is
prohibited.
ECCN:
9E991
COPYRIGHT
©
2017

### Page 2

MEB
-
57
-
02
Page
2
December
20
,
2017
Multi
-
engine
SER
VICE
BULLETIN
MEB
-
57
-
02
CONSUMABLE
MA
TERIAL
Y
ou
must
use
the
consumable
materials
that
follow
,
or
their
equivalent
,
to
complete
this
service
document.
NAME
NUMBER
MANUF
ACTURER
USE
Color
Chemical
Film
U074093
T
extron
A
viation
Parts
Distribution
7121
Southwest
Boulevard
Wichita
,
KS
67215
T
o
protect
bare
material
for
final
finish.
Corrosion
Resistant
Primer
K000574
T
extron
A
viation
Parts
Distribution
Final
finish
for
aluminum.
T
OOLING
No
specialized
tooling
is
required
to
complete
this
service
document.
WEIGHT
AND
BALANCE
INFORMA
TION
Negligible
REFERENCES
Cessna
Model
402C
(1979
-
1985)
Maintenance
Manual
Cessna
Model
414
/
414A
(1970
-
1985)
Service
Manual
Cessna
Model
421C
(1976
-
1985)
Service
Manual
NOTE:
T
o
make
sure
all
publications
used
are
complete
and
current.
Refer
to
www
.txtavsupport.com.
PUBLICA
TIONS
AFFECTED
None
ACCOMPLISHMENT
INSTRUCTIONS
1.
Prepare
the
airplane
for
maintenance.
A.
Make
sure
that
the
airplane
is
electrically
grounded.
B.
Make
sure
that
all
switches
are
in
the
OFF
/
NORM
position.
C.
Disconnect
electrical
power
from
the
airplane.
(1)
Disconnect
the
airplane
battery
.
(2)
Disconnect
external
electrical
power
.
D.
Attach
maintenance
warning
tags
to
the
battery
and
external
power
receptacle
that
have
"DO
NOT
CONNECT
ELECTRICAL
POWER
-
MAINTENANCE
IN
PROGRESS"
written
on
them.
2.
(If
592031
-
10
Panels
are
not
purchased.)
(Refer
to
Figure
1
,
Detail
B.)
Fabricate
the
access
panels.
A.
Cut
out
two
7.00
inch
by
8.00
inch
rectangles
from
the
S3806
-
1
1
Sheet
Material
or
ALCLAD
2024
-
T3.
B.
Radius
the
corners
0.25
inch.
C.
Identify
one
surface
on
each
of
the
panels
as
UP
.
D.
Roll
or
crimp
the
outer
0.25
inch
of
the
panel
upward
6°
around
the
perimeter
.
E.
Protect
the
fabricated
panels
with
U074093
Color
Chemical
Film
and
K000574
Corrosion
Resistant
Primer
.
3.
(If
5292031
-
19
Nutplate
Strips
are
not
purchased.)
(Refer
to
Figure
1
,
Detail
C.)
Fabricate
the
nutplate
strips.
A.
Cut
out
two
6.25
inch
by
0.65
inch
rectangles
from
the
S3806
-
1
1
Sheet
Material.
B.
Drill
three
equally
spaced
0.162
Inch
-
Diameter
Holes
in
each
strip.

### Page 3

Multi
-
engine
SER
VICE
BULLETIN
MEB
-
57
-
02
C.
Match
drill
the
six
0.098
Inch
-
Diameter
Holes
for
the
MS20426AD3
-
4A
Rivets
in
each
strip.
D.
Protect
the
strips
with
U074093
Color
Chemical
Film
and
K000574
Corrosion
Resistant
Primer
.
E.
Install
three
MS21075L06N
Nutplates
with
six
MS20426AD3
-
4A
Rivets
in
each
strip.
4.
(Refer
to
Figure
1
,
Detail
A.)
Make
the
cutout
in
the
lower
right
wing
skin.
NOTE:
The
cutout
dimension
is
identified
in
Figure
1
Detail
A.
A.
Identify
the
area
to
cut
the
lower
wing
skin
between
the
engine
and
fuselage
inboard
of
the
rib.
B.
Put
the
5292031
-
10
(or
fabricated)
Access
Panel
into
position
and
trace
the
outline
on
the
lower
wing
skin.
C.
Remove
the
rivets
that
are
inside
the
traced
panel
outline.
D.
Countersink
the
holes
where
the
rivets
were
removed
100°
x
0.190
inch
-
diameter
.
E.
Insert
a
piece
of
scrap
stainless
steel
between
the
lower
wing
skin
and
the
lower
forward
spar
cap
W
ARNING:
Do
not
damage
the
forward
spar
when
making
the
cutout
in
the
lower
wing
skin.
Any
damage
to
the
forward
spar
will
likely
required
spar
,
spar
cap
,
or
spar
fitting
replacement.
Premature
cracking
may
occur
if
damage
to
the
spar
,
spar
cap
,
or
spar
fitting
is
not
noticed.
Mechanics
should
use
great
care
and
caution
when
making
this
cutout.
Every
effort
must
be
made
to
protect
the
spar
,
spar
cap
,
and
spar
fitting
from
damage.
F
.
Make
the
cutout
in
the
lower
wing
skin
at
the
identified
area.
G.
Deburr
the
cutout.
H.
Remove
the
scrap
stainless
steel.
I.
Protect
the
edges
of
the
cutout
with
U074093
Color
Chemical
Film
and
K000574
Corrosion
Resistant
Primer
.
5.
(Refer
to
Figure
1
,
Detail
A.)
Install
the
nutplate
strip
on
the
right
wing.
A.
Put
the
5292031
-
19
(or
fabricated)
Nutplate
Strip
into
position
and
identify
the
hole
locations.
B.
Drill
two
Number
30
(0.128
inch
-
diameter)
holes
in
the
lower
wing
skin
and
5292031
-
19
(or
fabricated)
Nutplate
Strip.
C.
Match
drill
three
0.162
inch
-
diameter
holes
in
the
lower
wing
skin
that
align
with
the
nutplates
on
the
5292031
-
19
(or
fabricated)
Nutplate
Strip.
D.
Remove
the
5292031
-
19
(or
fabricated)
Nutplate
Strip.
E.
Deburr
the
drilled
holes.
F
.
Countersink
the
Number
30
(0.128
inch
-
diameter)
holes
100°
x
0.190
inch
-
diameter
.
G.
Protect
all
bare
material
with
U074093
Color
Chemical
Film
and
K000574
Corrosion
Resistant
Primer
.
H.
Install
one
5292031
-
19
(or
fabricated)
Nutplate
Strip
with
two
NAS1097AD4
-
5
Rivets.
6.
(Refer
to
Figure
1
,
Detail
A.)
Install
19
NAS1097AD4
-
6
Rivets
to
attach
the
skin
to
the
wing
structure
on
the
right
wing.
7.
(Refer
to
Figure
1
,
Detail
A.)
Install
the
access
panel
on
the
right
wing.
A.
Put
the
5292031
-
10
or
fabricated
Access
Panel
into
position
and
identify
the
hole
locations.
NOTE:
Make
sure
that
the
crimped
surface
of
the
panel
contacts
the
lower
wing
skin.
B.
Match
drill
three
Number
27
(0.144
inch
-
diameter)
holes
in
the
aft
portion
of
the
5292031
-
10
or
fabricated
Access
Panel
that
align
with
the
nutplates.
MEB
-
57
-
02
December
20
,
2017
Page
3

### Page 4

MEB
-
57
-
02
Page
4
December
20
,
2017
Multi
-
engine
SER
VICE
BULLETIN
MEB
-
57
-
02
C.
Match
drill
five
Number
10
(0.193
inch
-
diameter)
holes
in
the
forward
portion
of
the
5292031
-
10
or
fabricated
Access
Panel
that
align
with
the
nutplates.
D.
Deburr
the
drilled
holes.
E.
Dimple
five
Number
10
(0.193
inch
-
diameter)
holes
at
100°.
F
.
Enlarge
the
existing
countersinks
in
the
wing
skin
if
necessary
to
allow
the
5292031
-
10
(or
fabricated)
Access
Panel
to
sit
flush.
G.
Protect
the
5292031
-
10
(or
fabricated)
Access
Panel
with
U074093
Color
Chemical
Film
and
K000574
Corrosion
Resistant
Primer
.
H.
Paint
the
5292031
-
10
(or
fabricated)
Access
Panel
the
same
color
as
the
lower
surface
of
the
wing.
I.
Install
the
5292031
-
10
(or
fabricated)
Access
Panel
with
three
MS35206
-
230
Screws
and
five
MS24694
-
S153
Screws.
8.
Do
this
modification
again
for
the
left
wing.
9.
Remove
the
maintenance
warning
tags
and
connect
the
airplane
battery
.
10.
Make
an
entry
in
the
airplane
logbook
that
states
compliance
and
method
of
compliance
with
this
service
document.

### Page 5 (OCR)

Beechcrafi  Hawker
Multi-engine  SERVICE BULLETIN  Cessna
TEXTRON AVIATION
MEB-57-02
B21723
MS24694-S153
5292031-10  Screw  Center Cut Out
Access Panel  (5 Each Required)  Between Forward
(1 Required)  Spar Webs
NAS1097AD4-6  (NOTE 1)
Rivet  0.50
(19 Required)
0.60
(Typical)  (0 0)  (0 1)0)
1.94
(NOTE 2)
0.25 Inch
Radius
(Typical)
1.00
(Typical)  5292031-19
Nutplate Strip
→→  (1 Required)
0.162 Inch-Diameter Hole  • 0.35  C
Through Skin  6.31  (Typical)
MS35206-230  (NOTE 2)
Screw  - 1.19  Number 30
(3 Each Required)  (0.128 inch-diameter)
DETAIL A  NAS1097AD4-5  Hole Through Skin
FWD  Looking Up at Forward Spar  Rivet
•OUTBD  Right Side Shown, Left Side Opposite  (2 Required)
NOTE 1: All Dimensions are shown in inches.
NOTE 2: Dimension is for cutting out a section of the lower skin.
NOTE 3: Model 402 shown for illustrative purposes, other models are similar.  5910T3001
5292031
Figure 1. Access Panel Installation For Forward Spar (Sheet 1)
MEB-57-02
December 20, 2017  Page 5

### Page 6 (OCR)

Beechcraft  Hawker
Multi-engine  SERVICE BULLETIN  Cessna
TEXTRON ÀVIATION
MEB-57-02
B21724
8.00  0.25-Inch
Radius
Corners
Crimp edge
upward 6-degrees
by 0.125-inch
ЛА
7.00
Number 27
Number 10  (0.144 inch-diameter) Hole
(0.193 inch-diameter) Hole  (3 Required)
(5 Required)  Match-drill to align with
Match-drill to align with  the installed nutplates
the installed nutplates
DETAIL B
5292031-10 Access Panel
Fabricate from S3806-11
(0.05-Inch Alclad 2024-T3)
Crimp edge
upward 6-degrees
by 0.125-inch
VIEW A-A
B529T3021
AA529T3021
Figure 1. Access Panel Installation For Forward Spar (Sheet 2)
MEB-57-02
Page 6  December 20, 2017

### Page 7 (OCR)

Beechcraft  Hawker
Multi-engine SERVICE BULLETIN  Cessna
TEXTRON ÀVIATION
MEB-57-02
B21725
0.162 Inch-Diameter Hole
(Equally Spaced)
MS21075L06N
Nutplate
6.25  (3 Each Required)
200  0.65
0.32
(Typical)  2 Equal  →1.00
Spaces
0.093 (3/32) Inch-Diameter Hole
MS20426AD3-4A  Rivet  DETAIL C
(6 Each Required)  5292031-19 Nutplate Strip
Fabricate From S3806-9
(0.032-Inch Alclad 2024-T3)
NOTE: All Dimensions are shown in inches.  5910T3001  5291031
Figure 1. Access Panel Installation For Forward Spar (Sheet 3)
MEB-57-02
December 20, 2017  Page 7

### Page 8

MEB
-
57
-
02
Page
8
December
20
,
2017
Multi
-
engine
SER
VICE
BULLETIN
MEB
-
57
-
02
MA
TERIAL
INFORMA
TION
Order
the
kit
/
parts
below
to
install
this
modification.
NEW
P
/
N
QUANTITY
KEY
WORD
OLD
P
/
N
INSTRUCTIONS
/
DISPOSITION
MEB
-
57
-
02
1
Kit
,
consisting
of
the
following
parts:
MS24694
-
S153
10
Screw
Same
MS35206
-
230
6
Screw
None
NAS1097AD4
-
5
4
Rivet
None
NAS1097AD4
-
6
38
Rivet
MS20470AD4
-
6
MEB
-
57
-
02
1
Instructions
The
part
that
follows
is
required
to
complete
this
modification.
NEW
P
/
N
QUANTITY
KEY
WORD
OLD
P
/
N
INSTRUCTIONS
/
DISPOSITION
5292031
-
10
2
Access
Panel
None
5292031
-
19
2
Nutplate
Strip
None
If
5292032
-
4
Access
Panels
are
not
available
,
the
part
that
follows
can
be
used
to
fabricate
two
5292032
-
4
Access
Panels.
NEW
P
/
N
QUAN-
TITY
KEY
WORD
OLD
P
/
N
INSTRUCTIONS
/
DISPOSITION
S3806
-
1
1
1
Sheet
Material
None
Optional
to
fabricate
access
panel
If
5292031
-
19
Nutplate
Strips
are
not
available
,
in
addition
to
the
S3806
-
1
1
Sheet
Material
,
the
parts
that
follows
can
be
used
to
fabricate
two
5292031
-
19
Nutplate
Strips.
NEW
P
/
N
QUAN-
TITY
KEY
WORD
OLD
P
/
N
INSTRUCTIONS
/
DISPOSITION
MS20426AD3
-
4A
12
Rivet
None
Optional
to
fabricate
nutplate
strip
MS21075L06N
6
Nutplate
None
Optional
to
fabricate
nutplate
strip
S3806
-
9
1
Sheet
Material
None
Optional
to
fabricate
nutplate
strip
*
Please
contact
a
T
extron
A
viation
Authorized
Service
Facility
for
current
cost
and
availability
of
parts
listed
in
this
service
document.

### Page 9

Multi
-
engine
OWNER
ADVISOR
Y
MEB
-
57
-
02
TITLE
WINGS
-
ACCESS
P
ANEL
INST
ALLA
TION
FOR
FOR
W
ARD
SP
AR
T
O:
Cessna
Model
402C
,
414A
,
and
421C
Aircraft
Owner
REASON
Customers
have
requested
an
access
panel
to
gain
easy
access
to
the
forward
spar
for
inspections.
COMPLIANCE
OPTIONAL.
This
service
document
can
be
accomplished
at
the
discretion
of
the
owner
.
MA
TERIAL
A
V
AILABILITY
No
part
are
required
to
complete
this
service
document.
P
ART
NUMBER
A
V
AILABILITY
COST
MEB
-
57
-
02
*
*
MS20426AD3
-
4A
*
*
MS21075L06N
*
*
S3806
-
1
1
*
*
S3806
-
9
*
*
5292031
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10
*
*
5292031
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19
*
*
*
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MEB
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02
December
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