# Textron Aviation Mandatory Single Engine Service Letter SEL-57-08: Revision 1

- Rights: © Textron Aviation Inc. Filed by the FAA in regulations.gov docket FAA-2020-0156; AD 2020-03-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Textron Aviation Mandatory Single Engine Service Letter SEL-57-08](https://openairdocs.org/service-documents/cessna/sel57-08.md)
- Title as filed: sel-57-08r1
- Pages: 22
- PDF: https://openairdocs.org/files/sha256/d6/6d/d66dddf745e0231f48bad77dff19e5f8ef1e0522273b1c140b892a37a7a47947
- Page: https://openairdocs.org/service-documents/cessna/sel57-08/file/d66dddf745e0

## Text

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### Page 1

Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
REVISION
TRANSMITT
AL
This
sheet
transmits
Revision
1
to
SEL
-
57
-
08
,
which:
A.
Adds
additional
information
to
the
COMPLIANCE
section
and
clarify
inspection
compliance
and
references
to
SEL
-
57
-
06.
NOTE:
This
revision
replaces
the
original
issue
of
SEL
-
57
-
08
in
its
entirety
.
REVISION
COMPLIANCE
NO
EFFECT
.
Airplanes
previously
modified
by
this
service
letter
are
not
af
fected
by
this
revision.
LOG
OF
REVISIONS
Original
Issue
November
1
,
2019
Revision
1
November
19
,
2019
Original
Issue
-
November
1
,
2019
SEL
-
57
-
08
Revision
1
-
November
19
,
2019
Page
1
of
1
T
extron
A
viation
Customer
Service
,
P
.O.
Box
7706
,
Wichita
,
KS
67277
,
U.S.A.
1
-
316
-
517
-
5800
COPYRIGHT
©
2019

### Page 2

(No text on this page.)

### Page 3

Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
TITLE
WINGS
-
MODEL
210
CARR
Y
-
THRU
SP
AR
ONE
-
TIME
CORROSION
INSPECTION
EFFECTIVITY
MODEL
SERIAL
NUMBERS
210G
21058819
thru
21058936
T210G
T210
-
0198
thru
T210
-
0307
210H
21058937
thru
21059061
T210H
T210
-
0308
thru
T210
-
0392
210J
21059062
thru
21059199
T210J
21058140
,
T210
-
0393
thru
T210
-
0454
210K
21059200
thru
21059502
T210K
21059200
thru
21059502
210L
21059503
thru
21061573
T210L
21059503
thru
21061573
210M
21061574
thru
21062954
T210M
21061574
thru
21062954
210N
21062955
thru
21064897
P210N
P21000001
thru
P21000834
T210N
21062955
thru
21064897
210R
21064898
thru
21065009
P210R
P21000835
thru
P21000874
T210R
21064898
thru
21065009
REASON
The
carry
-
thru
spar
can
develop
corrosion
and
cracks.
Corrosion
can
propagate
and
lead
to
crack
development.
A
crack
in
the
carry
-
thru
spar
can
progress
to
a
point
that
a
structural
failure
of
the
carry
-
thru
spar
can
occur
,
resulting
in
loss
of
airplane
control
and
/
or
wing
separation.
Non
-
compliance
with
this
service
letter
may
result
in
undetected
corrosion
and
crack(s)
in
the
carry
-
thru
spar
,
which
can
result
in
structural
failure
of
the
carry
-
thru
spar
.
DESCRIPTION
This
service
document
provides
instructions
and
repair
criteria
to
do
a
detailed
inspection
of
the
carry
-
thru
spar
to
inspect
for
corrosion
and
/
or
cracks.
Original
Issue
-
November
1
,
2019
SEL
-
57
-
08
Revision
1
-
November
19
,
2019
Page
1
of
16
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
©
2019

### Page 4

SEL
-
57
-
08
Page
2
Revision
1
-
November
19
,
2019
Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
COMPLIANCE
W
ARNING:
The
Carry
-
Thru
spar
inspection
presented
in
this
service
letter
applies
to
airplanes
listed
in
the
Effectivity
Section.
The
compliance
time
is
for
unmodified
airplanes
,
and
represents
the
maximum
allowable
time.
Airplanes
that
have
been
modified
to
alter
the
airplane
design
,
gross
weight
,
or
airplane
performance
,
may
need
to
inspect
sooner
.
Examples
include
but
not
limited
to
the
following
common
supplemental
type
certificates
(STC’
s)
include
vortex
generators
,
wing
cuffs
,
ST
OL
kits
,
wing
tips
,
and
add
-
on
wing
fuel
tanks.
Contact
the
STC
holder
for
revised
inspection
intervals.
MANDA
T
OR
Y
.
Models
210G
,
T210G
,
210H
,
T210H
,
210J
,
T210J
,
210K
,
T210K
,
210L
,
T210L
,
210M
,
T210M:
This
service
letter
must
be
accomplished
within
20
flight
hours
or
next
Annual
Inspection
from
date
of
receipt
,
whichever
occurs
first.
Models
210N
,
P210N
,
T210N
,
210R
,
P210R
,
T210R:
This
service
letter
must
be
accomplished
within
200
flight
hours
or
the
next
Annual
Inspection
from
date
of
receipt
,
whichever
occurs
first.
Airplanes
which
have
complied
with
SEL
-
57
-
06
but
not
yet
with
this
service
letter
do
not
need
to
do
the
inspection
outlined
in
this
service
letter
,
however;
these
airplanes
need
to
complete
Steps
9
and
10
of
this
service
letter
within
200
flight
hours
or
at
the
next
annual
inspection
,
whichever
occurs
first.
Airplanes
which
have
not
complied
with
SEL
-
57
-
06
must
complete
this
service
letter
by
the
compliance
time
listed
for
the
appropriate
model.
After
this
service
letter
is
complied
with
,
the
inspection
outlined
in
SEL
-
57
-
06
does
not
need
to
be
complied
with.
If
the
inspection
form
associated
with
this
service
letter
or
SEL
-
57
-
06
has
not
been
sent
in
,
send
it
in
whether
or
not
cracks
or
corrosion
were
found.
Refer
to
the
Carry
-
Thru
Spar
Inspection
Report
for
contact
information.
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
.

### Page 5

Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
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
T
reatment
U074093
(Alodine
1
132
T
ouch
n
Prep)
T
extron
A
viation
Parts
Distribution
7121
Southwest
Boulevard
Wichita
,
KS
67215
T
o
prepare
bare
aluminum
surface
for
intermediate
primer
.
Corrosion
Resistant
Primer
K000574
(2oz
Kit)
T
extron
A
viation
Parts
Distribution
T
ouch
-
up
primer
kit.
Cor
-
Ban
23
COR
-
BAN
-
23
(U074098)
(12oz
aerosol)
T
extron
A
viation
Parts
Distribution
Corrosion
Inhibiting
Compound
coating.
Formit
-
18
Fan
Formit
-
18
T
extron
A
viation
Parts
Distribution
Nozzle
for
Cor
-
Ban
23
application.
Primer
,
Epoxy
Polyamide
(Primer)
K000479
(2
Gal
Kit)
T
extron
A
viation
Parts
Distribution
Large
primer
kit.
Aluminum
oxide
paper
or
cloth
(high
purity)
-
180
or
220
,
and
320
grit
Commercially
A
vailable
For
paint
/
corrosion
removal
and
surface
preparation
before
painting.
Conversion
Coating
Bonderite
M
-
CR
600R
TU
Commercially
available
Conversion
Coating
of
bare
metal
before
intermediate
primer
.
Extreme
Simple
Green
Aircraft
and
Precision
Cleaner
Commercially
A
vailable
Initial
cleaning
of
soiled
surface.
Isopropyl
Alcohol
Commercially
A
vailable
T
ype
I
Cleaning
Solvent
for
surface
cleaning
prior
to
painting.
Methyl
Propyl
Ketone
Commercially
A
vailable
Cleaning
solvent
of
Corban
Corrosion
Inhibiting
Compound.
CAUTION:
Do
not
use
any
other
Simple
Green
products
other
than
Extreme
Simple
Green
as
some
have
been
found
to
be
corrosive.
NOTE:
T
extron
A
viation
has
tested
and
approved
Cor
-
Ban
35
and
ARDROX
A
V
-
8.
These
products
may
be
used
in
place
of
Cor
-
Ban
23
at
the
owners
discretion.
T
OOLING
NAME
NUMBER
MANUF
ACTURER
USE
10X
Magnifying
Lense
Commercially
A
vailable
For
detailed
visual
inspection
of
carry
-
thru
spar
.
Micrometer
(depth
gauge
style)
Commercially
A
vailable
T
o
measure
depth
of
blended
areas
of
carry
thru
spar
.
Eddy
Current
Inspection
Equipment
Nondestructive
Inspection
Methods
and
Requirements
,
Document
2A
-
13
-
01
found
in
Section
2A
Supplemental
Inspection
Documents
in
the
appropriate
Model
Service
or
Maintenance
Manual
For
Eddy
Current
inspection
of
carry
-
thru
spar
lower
surface.
SEL
-
57
-
08
Revision
1
-
November
19
,
2019
Page
3

### Page 6

SEL
-
57
-
08
Page
4
Revision
1
-
November
19
,
2019
Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
REFERENCES
Cessna
Model
200
Series
(1966
-
1968)
Service
Manual
Cessna
Model
210
Centurion
Series
(1969)
Service
Manual
Cessna
Model
210
Centurion
Series
(1970
-
1976)
Service
Manual
Cessna
Model
210
and
T210
Series
(1977
-
1984)
Service
Manual
Cessna
Model
210
and
T210
Series
(1985
-
1986)
Service
Manual
Cessna
Model
P210
Series
(1978
-
1983)
Service
Manual
Cessna
Model
P210
Series
(1985
-
1986)
Service
Manual
Inspection
T
ime
Limits
-
Structure
,
Section
2A
-
10
-
00
found
in
Section
2A
Supplemental
Inspection
Documents
in
the
appropriate
Model
Service
or
Maintenance
Manual
,
Nondestructive
Inspection
Methods
and
Requirements
,
Document
2A
-
13
-
01
found
in
Section
2A
Supplemental
Inspection
Documents
in
the
appropriate
Model
Service
or
Maintenance
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
external
electrical
power
.
(2)
Disconnect
the
airplane
battery
.
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.
Remove
the
pilot
and
co
-
pilot
seats
if
necessary
.
(Refer
to
the
applicable
Model
Service
or
Maintenance
Manual.)
3.
Get
access
to
all
surfaces
of
the
carry
-
thru
spar
by
removing
panels
,
upholstery
,
headliner
,
sealant
,
and
installed
utility
or
oxygen
systems
as
necessary
.
(Refer
to
the
applicable
Model
Service
or
Maintenance
Manual.)
4.
Remove
foam
from
bottom
of
carry
-
thru
spar
as
applicable.
A.
Clean
all
adhesive
residue
from
the
carry
-
thru
spar
with
a
non
-
metallic
scraper
tool.
5.
Clean
grime
or
debris
from
all
interior
surfaces
of
the
carry
-
thru
spar
with
special
emphasis
on
lower
cap
surface.

### Page 7

Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
6.
(Refer
to
Figure
1
,
Sheets
1
-
5.)
Do
a
detailed
visual
inspection
of
the
carry
-
thru
spar
with
a
10X
magnification
lens
looking
for
corrosion
,
nicks
,
gouges
,
drill
starts
,
or
hardware
damage
and
must
include:
1.
The
visible
surfaces
of
the
Upper
cap.
2.
The
Spar
web
(include
cap
to
web
radius).
3.
The
Lower
cap
(include
upper
and
lower
surface
and
cap
edge).
NOTE:
The
detailed
visual
inspection
should
pay
particular
attention
to
locations
where
air
ducts
,
support
wires
,
and
upholstery
pads
contact
the
lower
spar
structure
as
well
as
lower
spar
cap
lower
surface
"Kick
Area"
between
BL
10.0
and
BL
12.5.
(Refer
to
the
figure
titled
Spar
Dimensions
after
T
able
1.)
A.
(Refer
to
Figure
1
,
Sheets
4
and
5.)
If
stress
corrosion
cracking
or
exfoliation
corrosion
(flaking)
of
the
spar
is
found
,
contact
T
extron
A
viation
T
eam
Structures
for
evaluation.
(Refer
to
the
Carry
-
Thru
Spar
Inspection
Report
for
contact
information.)
B.
If
corrosion
is
found
on
the
carry
-
thru
spar
,
the
area
can
be
reworked
as
follows:
NOTE:
If
previous
evidence
of
blending
can
be
determined
or
is
recorded
in
the
aircraft
log
book
for
the
same
location
corrosion
has
been
found
,
contact
T
extron
A
viation
Structures.
(1)
Use
180
grit
or
finer
aluminum
oxide
abrasive
paper
,
cloth
or
pads
to
carefully
remove
corrosion
and
blend
that
area
locally
around
the
af
fected
region.
(2)
Make
sure
to
only
remove
the
minimum
material
necessary
to
blend
the
corroded
surface
with
the
surrounding
surface.
(3)
Maintain
a
minimum
of
20:1
blend
to
depth
ratio.
(4)
Leave
no
sharp
edges
after
blending.
(5)
Finish
with
a
320
grit
or
finer
grained
aluminum
oxide
sandpaper
to
63
micro
RA
or
smoother
.
NOTE:
When
320
grit
is
properly
used
,
it
will
produce
a
63
micro
RA
surface
finish.
(6)
Use
a
vacuum
to
remove
dust.
(7)
Use
a
clean
cloth
wet
with
isopropyl
alcohol
to
clean
the
surface.
(8)
Measure
the
depth
of
the
blended
area
mechanically;
such
as
with
a
straight
edge
and
feeler
gauge
or
a
depth
gauge
micrometer
.
(a)
If
material
removed
is
greater
than
what
is
listed
in
the
T
ABLE
1
for
the
specific
spar
feature
,
contact
T
extron
A
viation
T
eam
Structures
with
the
dimension
of
blended
area
for
evaluation.
(Refer
to
the
Carry
-
Thru
Spar
Inspection
Report
for
contact
information.)
(b)
If
material
removed
is
less
than
0.010
inch
for
the
specific
spar
feature
in
T
ABLE
1
,
go
to
Step
8.
(c)
If
material
removed
is
greater
than
0.010
but
less
than
what
is
listed
in
T
ABLE
1
for
the
specific
spar
feature
,
complete
the
eddy
current
inspection
of
the
blended
areas
and
the
Kick
Area
from
buttock
line
10.0
thru
12.5
inch
(whether
there
is
or
is
not
presence
of
corrosion
in
the
Kick
Area)
,
go
to
Step
7.
SEL
-
57
-
08
Revision
1
-
November
19
,
2019
Page
5

### Page 8

SEL
-
57
-
08
Page
6
Revision
1
-
November
19
,
2019
Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
T
ABLE
1
REP
AIR
CRITERIA
Carry
-
thru
Spar
Feature
Spar
Buttock
Line
(BL)
(in)
Blend
Limit
(in)
Description
Center
Line
to
10.0
0.030
Spar
Constant
Cross
Section
10.0
to
12.5
0.030
Lower
Cap
Kick
Area
1
Lower
Cap
-
Lower
Surface
(1)
12.5
to
21.5
0.030
Outboard
of
Lower
Cap
Kick
Area
2
Lower
Cap
-
Upper
Surface
(1)
Center
Line
to
16.5
0.030
Spar
Constant
Cross
-
Section
thru
Cap
Kick
Area
3
Lower
Cap
Edge
(1)
Center
Line
to
16.5
0.100
Forward
or
Aft
facing
cap
edges
4
Lower
Cap
to
W
eb
Radius
(1)
Center
Line
to
16.5
0.030
(2)
Forward
or
Aft
facing
web
radii
5
Spar
W
eb
(1)
Center
Line
to
16.5
0.050
(2)
Includes
areas
common
to
web
holes
NOTE:
Dimensions
shown
are
in
Inches.
(1)
Limits
can't
be
combined
at
the
same
Buttock
Line
location
without
contacting
T
extron
A
viation.
Example:
W
eb
blend
and
a
lower
spar
cap
blend
cannot
be
combined
at
same
Buttock
Line
location
without
contacting
T
extron
A
viation.
(2)
The
carry
-
thru
spar
must
be
replaced
if
the
blend
limit
is
exceeded
in
this
area.
SP
AR
DIMENSIONS

### Page 9

Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
SP
AR
DET
AIL
C.
If
no
corrosion
is
found
on
the
carry
-
thru
spar
but
previous
evidence
of
blending
can
be
determined
or
is
recorded
in
the
aircraft
log
book
,
contact
T
extron
A
viation
Structures.
D.
If
no
corrosion
is
found
on
the
carry
-
thru
spar
,
go
to
Step
8.
7.
(Refer
to
Figure
1
,
V
iew
A
-
A.)
(If
corrosion
was
found
and
blended.)
Do
an
eddy
current
inspection
of
the
blended
area
as
follows:
(Refer
to
2A
-
13
-
01
,
Nondestructive
Inspection
Methods
and
Requirements
in
the
appropriate
Model
Service
or
Maintenance
Manual.)
A.
Plan
out
the
inspection
process
to
cover
the
items
listed
as
follows:
•
If
the
eddy
current
inspection
is
performed
by
qualified
personnel
that
are
not
representing
an
F
AA
Certified
Repair
Station
,
an
A&P
Mechanic
may
supervise
the
inspection
and
make
the
appropriate
logbook
entry
.
•
T
echnician
must
be
at
least
Level
2
certified.
•
Eddy
current
inspection
will
cover
the
carry
-
thru
spar
where
corrosion
was
blended
and
extend
1
Inch
beyond
the
blended
area
and
will
also
cover
the
lower
cap
spar
Kick
Area
from
Buttock
Line
10.0
thru
12.5.
•
Eddy
current
inspection
will
be
with
a
0.125
Inch
probe.
•
T
echnician
should
use
an
inspection
approach
that
ensures
the
entire
blended
surface
is
inspected
without
gaps
and
inspection
area
should
extend
1
Inch
beyond
the
blended
area
in
all
directions.
•
Limit
the
inspection
area
to
no
wider
than
4
square
inches
at
a
time
,
depending
on
size
of
blended
area.
Once
an
area
is
complete
,
move
to
any
additional
rework
location
and
repeat
the
eddy
current
inspection.
•
Inspect
one
section
at
time
and
overlap
each
section
by
0.25
Inch
overlap
between
each
section
and
identify
when
each
section
is
complete.
•
Identify
when
each
section
is
complete
to
help
keep
track
of
progress.
B.
Review
the
General
Requirements
and
Eddy
Current
Inspection
sections
of
2A
-
13
-
01
Nondestructive
Inspection
Methods
and
Requirements.
C.
Calibrate
the
eddy
current
instrument
-
Impedance
Plane.
(Refer
to
2A
-
13
-
01
,
Nondestructive
Inspection
Methods
and
Requirements
,
Section
2.
Eddy
Current
Inspection.)
SEL
-
57
-
08
Revision
1
-
November
19
,
2019
Page
7

### Page 10

SEL
-
57
-
08
Page
8
Revision
1
-
November
19
,
2019
Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
D.
Eddy
current
scan
the
blended
surface
with
an
0.125
Inch
diameter
surface
pencil
probe
at
200
kHz.
•
Scan
direction
must
be
with
an
inboard
to
outboard
direction.
•
Use
of
a
non
-
metallic
straight
edge
as
a
guide
will
help
ensure
there
is
not
a
fore
-
aft
motion
of
the
probe.
•
Probe
one
small
section
of
only
a
couple
of
inches
at
a
time
,
recommend
no
wider
than
4
Inches.
•
Move
the
probe
in
0.125
Iinch
increments.
•
Overlap
each
section
by
0.25
Inch.
•
Extend
1
Inch
beyond
the
blended
area.
(1)
Look
for
a
sharp
response
of
10
-
percent
screen
height
or
more
which
may
indicate
corrosion
or
fatigue
cracking
or
both.
E.
If
you
find
one
or
more
cracks
,
further
flight
is
NOT
permitted.
Y
ou
must
replace
the
carry
-
thru
spar
before
further
flight.
8.
Provide
the
results
of
the
detailed
visual
and
eddy
current
inspections
to
T
extron
A
viation
,
T
eam
Structures.
Use
the
Carry
-
Thru
Spar
Inspection
Report
form
and
pictures
as
applicable.
T
elephone
number
and
email
address
are
provided
on
the
form.
NOTE:
The
Carry
-
Thru
Spar
Inspection
Report
form
must
be
sent
to
T
extron
A
viation
T
eam
Structures
to
report
all
conditions
,
cracks
,
corrosion
,
or
no
cracks
,
no
corrosion.
9.
Apply
protective
coatings
to
the
carry
-
thru
spar
as
follows:
NOTE:
The
steps
that
follow
are
for
the
carry
-
thru
spar
located
inside
the
fuselage.
Rework
can
be
from
the
removal
and
/
or
blending
of
corrosion
,
nicks
,
gouges
,
drill
starts
,
or
hardware
damage
,
anything
that
would
result
in
the
exposure
of
bare
metal
by
removal
of
the
coatings.
A.
If
there
has
been
rework
and
the
carry
-
thru
spar
was
not
entirely
primed
before
the
inspection:
(1)
Wipe
the
entire
surface
with
clean
wiping
cloths
wet
with
isopropyl
alcohol.
(a)
Let
the
surface
dry
.
(2)
Apply
Conversion
coating
(Bonderite
M
-
CR
600R
TU)
to
the
entire
carry
-
thru
spar
surface
following
the
manufacture
directions
for
application
and
dry
time.
(3)
Apply
a
epoxy
primer
(primer
coat)
to
the
entire
surface
following
the
manufacture
directions
for
application
and
dry
time.
(4)
Go
to
Step
10.
B.
If
there
has
been
rework
and
the
carry
-
thru
spar
was
entirely
primed
before
the
inspection:
(1)
Wipe
the
areas
with
bare
metal
surface
with
clean
wiping
cloths
wet
with
isopropyl
alcohol.
(a)
Let
the
parts
dry
.
(2)
Apply
Chemical
Film
T
reatment
(Alodine
1
132)
to
the
areas
with
bare
metal
surface
following
the
manufacture
directions
for
application
and
dry
time.
(3)
Apply
a
epoxy
primer
(primer
coat)
to
the
bare
metal
surface
following
the
manufacture
directions
for
application
and
dry
time.
(4)
Go
to
Step
10.
C.
If
there
was
not
rework
and
the
carry
-
thru
spar
was
not
entirely
primed
before
the
inspection:
(1)
Wipe
the
entire
surface
with
clean
wiping
cloths
wet
with
isopropyl
alcohol.
(a)
Let
the
surface
dry
.
(2)
Apply
Conversion
coating
(Bonderite
M
-
CR
600R
TU)
to
the
entire
surface
following
the
manufacture
directions
for
application
and
dry
time.
(3)
Apply
a
epoxy
primer
(primer
coat)
to
the
entire
surface
following
the
manufacture
directions
for
application
and
dry
time.

### Page 11

Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
(4)
Go
to
Step
10.
D.
If
there
was
not
rework
and
the
carry
-
thru
spar
was
entirely
primed
before
the
inspection:
(1)
Go
to
Step
10.
10.
Apply
Corrosion
Inhibiting
Compound
(CIC)
to
the
entire
surface
of
the
carry
-
thru
spar
that
is
accessible
in
the
fuselage
as
follows:
(Refer
to
SEL
-
51
-
01
Standard
Practices
-
Structures
-
Use
of
Corrosion
Inhibiting
Compounds.)
NOTE:
SEL
-
51
-
01
is
a
resource
that
provides
additional
detailed
information
about
the
application
process
of
CIC
such
as
equipment
,
facility
,
cleaning
,
masking
,
and
application
processes.
A.
Mask
areas
around
the
carry
-
thru
spar
areas
to
prevent
over
spray
of
the
CIC.
B.
Spray
aerosol
with
extension
tube
to
minimize
over
spray
.
C.
Apply
the
CIC
in
one
full
wet
coat.
D.
Some
sag
/
run
is
acceptable.
A
spot
of
significant
sag
/
run
needs
to
be
cleaned
by
MPK
(methyl
propyl
ketone)
wiping
and
the
CIC
shall
be
reapplied.
E.
W
et
film
thickness
of
CIC
is
approximately
1
to
2
mils
for
Cor
-
Ban
23.
NOTE:
The
coating
should
be
tack
-
free
after
two
to
three
hours.
F
.
After
the
CIC
coating
is
tack
-
free
,
remove
the
masking
from
around
the
application
area.
G.
Let
the
CIC
coating
cure
with
a
minimum
cure
temperature
no
less
than
50
degrees
F
.
1
1.
Install
removed
utility
systems
,
oxygen
systems
,
headliner
and
upholstery
that
was
removed
to
access
the
carry
-
thru
spar
.
(Refer
to
the
applicable
Model
Service
or
Maintenance
Manual.)
NOTE:
The
installation
of
the
foam
padding
to
the
bottom
of
the
carry
-
thru
spar
is
optional
however;
the
headliner
final
fit
may
dif
fer
if
the
foam
padding
is
not
installed.
12.
Install
the
pilot
and
co
-
pilot
seats
if
removed.
(Refer
to
the
applicable
Model
Service
or
Maintenance
Manual.)
13.
Remove
the
maintenance
warning
tags
and
connect
the
airplane
battery
.
14.
Make
an
entry
in
the
airplane
logbook
that
states
compliance
and
method
of
compliance
with
this
service
document.
SEL
-
57
-
08
Revision
1
-
November
19
,
2019
Page
9

### Page 12 (OCR)

Single  Beechcraft  Hawker
Engine  SERVICE LETTER  Cessna
TEXTRON AVIATION
MANDATORY  SEL-57-08
B21885
Carry-Thru
Spar
Wing
Attachment Lug
DETAIL A
1210T1036
A1210X1037
Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 1)
SEL-57-08
Page 10  Revision 1 - November 19, 2019

### Page 13 (OCR)

Single  Beechcraft  Hawker
Engine  SERVICE LETTER  Cessna
TEXTRON AVIATION
MANDATORY  SEL-57-08
B21886
Blended Area
Eddy Current Pencil Probe
VIEW A-A
View Looking Up at Lower Surface of the Carry-Thru
NOTE: Eddy Current Pencil Probe motion of travel is center to outboard
while working small equally spaced overlapping sections.
Eddy current inspection will cover the lower surface of the carry-thru
spar where corrosion was blended and extend 1 Inch beyond the
blended area. This inspection technique also applies to the Kick area.
2110068-1
Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 2)
SEL-57-08
Revision 1 - November 19, 2019  Page 11

### Page 14 (OCR)

Single  Beechcraft  Hawker
Engine  SERVICE LETTER  Cessna
TEXTRON AVIATION
MANDATORY  SEL-57-08
B21887
0.064 Inch
2.5 mm
Corrosion Pitting on Lower Surface of Carry-Thru Spar
NOTE: Image not to scale.
Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 3)
SEL-57-08
Page 12  Revision 1 - November 19, 2019

### Page 15 (OCR)

Single  Beechcraft  Hawker
Engine  SERVICE LETTER  Cessna
TEXTRON AVIATION
MANDATORY  SEL-57-08
B21888
Stress Corrosion Cracking on Spar Cap
Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 4)
SEL-57-08
Revision 1 - November 19, 2019  Page 13

### Page 16 (OCR)

Engine  Single  SERVICE LETTER  Beechcraft  Cessna  Hawker
TEXTRON AVIATION
MANDATORY  SEL-57-08
B21889
Exfoliation
Exfoliation Corrosion on Spar Cap
Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 5)
SEL-57-08
Page 14  Revision 1 - November 19, 2019

### Page 17 (OCR)

Single  Beechcraft  Hawker
Engine  SERVICE LETTER  Cessna
TEXTRON AVIATION
MANDATORY  SEL-57-08
B21974
currently primed?  No  Prime & Apply CIC to  Entire Spar Internal to
Yes  Fuselage
No  (above upper limits)  Scrap Spar  Apply CIC to Entire Spar  Internal to Fuselage  SEL Compliance
No
Process Flow Chart  (Reference Only)  Corrosion Found?  No  (above blend limit  but not upper limit)  Contact TXTAV  Field Repair or  Scrap Spar  Apply CIC to Entire Spar Internal to
Fuselage
Yes  (between 0.010" & limit)  Blend Corrosion  NDI Blend  Locations & Lower  Spar Kick
Yes
Corrosion within  table limits?  Yes  (below 0.010")  Blend Corrosion  No NDI  Chem Film  Blended Areas  Unprimed spars get all  surfaces primed / Primed  spars get reworked  areas spot primed
Figure 2. PROCESS FLOW CHART (REFERENCE) (Sheet 1)
SEL-57-08
Revision 1 - November 19, 2019  Page 15

### Page 18

SEL
-
57
-
08
Page
16
Revision
1
-
November
19
,
2019
Single
Engine
SER
VICE
LETTER
MANDA
T
OR
Y
SEL
-
57
-
08
MA
TERIAL
INFORMA
TION
No
parts
are
required
to
complete
this
service
document.

### Page 19

Single
Engine
A
TT
ACHMENT
MANDA
T
OR
Y
SEL
-
57
-
08
CARR
Y
-
THRU
SP
AR
INSPECTION
REPORT
T
o:
Page:
1
of
___
Pages
Wichita
Citation
Service
Center
Includes
this
cover
sheet
Attn:
T
extron
A
viation
T
eam
Structures
2121
S.
Hoover
Rd
Registration
No.:
Wichita
,
Kansas
67209
T
otal
T
ime
in
Service
(Hrs.):
Phone
Number:
316
-
517
-
6061
email:
structures@txtav
.com
Facility
Name:
Facility
Address:
From:
Date:
Airplane
Serial
Number:
Owner's
Name:
Phone
Number
of
Facility:
Owner's
Address:
Fax
Number
of
Facility:
Owner's
Phone
Number:
Owner's
Fax
Number:
Please
provide
detailed
and
dimensioned
descriptions
of
any
crack(s)
or
corrosion.
Attach
pictures
to
this
form
as
necessary
.
Comments
/
Notes:
Cracks:
Y
es
No
(Circle
One)
Corrosion:
Y
es
No
(Circle
One)
Airplane
Operation:
Severe:
Y
es
No
(Circle
One)
T
ypical:
Y
es
No
(Circle
One)
Unknown:
Y
es
No
(Circle
One)
Any
previously
known
or
recorded
blending
or
material
removal
on
the
carry
-
thru
spar?
Y
es
No
(Circle
One)
List
any
Structural
Supplemental
T
ype
Certificates
(STC's)
Installed:

### Page 20

(No text on this page.)

### Page 21

Single
Engine
OWNER
ADVISOR
Y
SEL
-
57
-
08
TITLE
WINGS
-
MODEL
210
CARR
Y
-
THRU
SP
AR
ONE
-
TIME
CORROSION
INSPECTION
T
O:
Cessna
Model
210G
,
T210G
,
210H
,
T210H
,
210J
,
T210J
,
210K
,
T210K
,
210L
,
T210L
,
210M
,
T210M
,
210N
,
P210N
,
T210N
,
210R
,
P210R
,
T210R
Aircraft
Owner
REASON
The
carry
-
thru
spar
can
develop
corrosion
and
cracks.
Corrosion
can
propagate
and
lead
to
crack
development.
A
crack
in
the
carry
-
thru
spar
can
progress
to
a
point
that
a
structural
failure
of
the
carry
-
thru
spar
can
occur
,
resulting
in
loss
of
airplane
control
and
/
or
wing
separation.
Non
-
compliance
with
this
service
letter
may
result
in
undetected
corrosion
and
crack(s)
in
the
carry
-
thru
spar
,
which
can
result
in
structural
failure
of
the
carry
-
thru
spar
.
COMPLIANCE
W
ARNING:
The
Carry
-
Thru
spar
inspection
presented
in
this
service
letter
applies
to
airplanes
listed
in
the
Effectivity
Section.
The
compliance
time
is
for
unmodified
airplanes
,
and
represents
the
maximum
allowable
time.
Airplanes
that
have
been
modified
to
alter
the
airplane
design
,
gross
weight
,
or
airplane
performance
,
may
need
to
inspect
sooner
.
Examples
include
but
not
limited
to
the
following
common
supplemental
type
certificates
(STC’
s)
include
vortex
generators
,
wing
cuffs
,
ST
OL
kits
,
wing
tips
,
and
add
-
on
wing
fuel
tanks.
Contact
the
STC
holder
for
revised
inspection
intervals.
MANDA
T
OR
Y
.
Models
210G
,
T210G
,
210H
,
T210H
,
210J
,
T210J
,
210K
,
T210K
,
210L
,
T210L
,
210M
,
T210M:
This
service
letter
must
be
accomplished
within
20
flight
hours
or
next
Annual
Inspection
from
date
of
receipt
,
whichever
occurs
first.
Models
210N
,
P210N
,
T210N
,
210R
,
P210R
,
T210R:
This
service
letter
must
be
accomplished
within
200
flight
hours
or
the
next
Annual
Inspection
from
date
of
receipt
,
whichever
occurs
first.
Airplanes
which
have
complied
with
SEL
-
57
-
06
but
not
yet
with
this
service
letter
do
not
need
to
do
the
inspection
outlined
in
this
service
letter
,
however;
these
airplanes
need
to
complete
Steps
9
and
10
of
this
service
letter
within
200
flight
hours
or
at
the
next
annual
inspection
,
whichever
occurs
first.
Airplanes
which
have
not
complied
with
SEL
-
57
-
06
must
complete
this
service
letter
by
the
compliance
time
listed
for
the
appropriate
model.
After
this
service
letter
is
complied
with
,
the
inspection
outlined
in
SEL
-
57
-
06
does
not
need
to
be
complied
with.
If
the
inspection
form
associated
with
this
service
letter
or
SEL
-
57
-
06
has
not
been
sent
in
,
send
it
in
whether
or
not
cracks
or
corrosion
were
found.
Refer
to
the
Carry
-
Thru
Spar
Inspection
Report
for
contact
information.
Original
Issue
-
November
1
,
2019
SEL
-
57
-
08
Revision
A
-
November
19
,
2019
Page
1
of
2
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
©
2019

### Page 22

SEL
-
57
-
08
Page
2
Revision
A
-
November
19
,
2019
Single
Engine
OWNER
ADVISOR
Y
SEL
-
57
-
08
LABOR
HOURS
For
planning
purposes
only:
WORK
PHASE
LABOR
-
HOURS
Inspection
As
Necessary
W
ARRANTY
None
NOTE:
As
a
convenience
,
service
documents
are
now
available
online
to
all
our
customers
through
a
simple
,
free
-
of
-
charge
registration
process.
If
you
would
like
to
sign
up
,
please
visit
the
Customer
Access
link
at
www
.txtavsupport.com
to
register
.

---
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