# Beechcraft Service Letter MTL-27-07: No revision named

- Rights: © Textron Aviation Inc. Filed by the FAA in regulations.gov docket FAA-2025-3424; AD 2025-20-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Beechcraft Service Letter MTL-27-07](https://openairdocs.org/service-documents/beechcraft/mtl27-07.md)
- Title as filed: Beechcraft Mandatory Service Letter MTL-27-07
- Pages: 10
- PDF: https://openairdocs.org/files/sha256/12/ce/12ce6f2b8136d361f7c4ce6679c10e91e7c57b906552ee10658ca377c8afabb7
- Page: https://openairdocs.org/service-documents/beechcraft/mtl27-07/file/12ce6f2b8136

## Text

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### Page 1

Beechcraft
SER
VICE
LETTER
MANDA
T
OR
Y
MTL
-
27
-
07
TITLE
FLIGHT
CONTROLS
-
PILOT
AND
COPILOT
RUDDER
PEDAL
PUSHROD
LINKAGE
INSPECTION
EFFECTIVITY
MODEL
SERIAL
NUMBERS
B200GT
BY
-
335
,
BY
-
356
,
BY
-
443
,
BY
-
453
,
BY
-
454
B200CGT
BZ
-
4
thru
BZ
-
9
B300
FL
-
1
173
thru
FL
-
1
175
,
FL
-
1
177
,
FL
-
1
181
,
FL
-
1
184
thru
FL
-
1
186
,
FL
-
1
189
,
FL
-
1
193
,
FL
-
1
197
thru
FL
-
1202
,
FL
-
1210
,
FL
-
121
1
,
FL
-
1213
,
FL
-
1218
,
FL
-
1220
thru
FL
-
1222
,
FL
-
1225
,
FL
-
1228
thru
FL
-
1230
,
FL
-
1232
,
FL
-
1233
,
FL
-
1240
thru
FL
-
1242
,
FL
-
1244
,
FL
-
1245
,
FL
-
1249
thru
FL
-
1251
,
FL
-
1253
,
FL
-
1257
thru
FL
-
1259
,
FL
-
1262
,
FL
-
1265
,
FL
-
1266
,
FL
-
1269
,
FL
-
1271
,
FL
-
1275
,
FL
-
1276
,
FL
-
1277
,
FL
-
1280
,
FL
-
1284
,
FL
-
1286
,
FL
-
1287
,
FL
-
1290
,
FL
-
1291
,
FL
-
1293
,
FL
-
1296
,
FL
-
1305
,
FL
-
1310
,
FL
-
1315
thru
FL
-
1317
,
FL
-
1319
,
FL
-
1320
B300C
FM
-
78
thru
FM
-
86
,
FM
-
88
,
FM
-
90
thru
FM
-
92
,
FM
-
94
,
FM
-
96
thru
FM
-
107
,
FM
-
1
10
NOTE:
The
airplanes
listed
in
the
ef
fectivity
above
that
have
the
digital
flight
data
recorder
,
DFDR
,
installed
are
af
fected
by
this
service
document.
REASON
During
installation
of
the
rudder
pushrod
rod
end
the
incorrect
type
of
rivet
that
attaches
the
rod
end
may
have
been
installed.
If
the
incorrect
rivet
was
installed
this
could
cause
the
rudder
pushrod
tube
to
separate
from
the
rod
end.
Failure
to
comply
can
result
in
loss
of
rudder
control
which
can
result
in
loss
of
control
of
the
airplane
during
flight
or
ground
operations.
DESCRIPTION
This
service
document
provides
parts
and
instructions
to
inspect
the
pilots
and
copilot's
rudder
pushrods
for
the
correct
rivets
and
replace
them
as
required.
COMPLIANCE
MANDA
T
OR
Y
.
This
service
document
must
be
accomplished
on
airplanes
that
have
the
DFDR
installed.
NOTE:
Any
identified
soft
rivet
(no
marking)
regardless
of
rivet
location
and
/
or
left
and
right
pushrods
,
must
be
replaced
in
the
time
stated
within
the
compliance
section
•
No
mark
(alloy
code
A):
1
100
or
3003
pure
aluminum
•
Dimple
(alloy
code
AD)
21
17
aluminum
alloy
MTL
-
27
-
07
July
25
,
2025
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
©
2025

### Page 2

MTL
-
27
-
07
Page
2
July
25
,
2025
Beechcraft
SER
VICE
LETTER
MANDA
T
OR
Y
MTL
-
27
-
07
Criteria
Compliance
T
ime
Inspection
Within
20
flight
hours
or
30
days
from
the
service
document
date
,
which
ever
occurs
first.
If
2
soft
rivets
are
found
adjacent
to
each
other
on
the
same
rod
end
for
one
pushrod.
Before
next
flight.
If
1
soft
rivet
and
1
hard
rivet
are
installed
on
any
of
the
4
rod
ends.
Within
200
flight
hours
or
12
month
inspection
,
which
ever
occurs
first.
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)
If
the
aircraft
serial
number
is
identified
within
the
(Ef
fectivity
Section)
,
the
mechanic
must
use
all
technical
data
while
accomplishing
the
instructions
within
this
service
document.
The
mechanic
must
maintain
compliance
to
aviation
acceptable
standard
practices
and
regulations
(CFR).
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.
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
.
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
Corrosion
Resistant
Primer
Graco
Supply
Company
2056
S.
Edwards
Ste.
C
Wichita
,
KS
67213
Corrosion
Resistant
Primer
.
Color
Chemical
Film
T
reatment
U074093
(Alodine
1
132
T
ouch
n
Prep)
T
extron
A
viation
Parts
Distribution
WW2.TXT
A
V
.COM
/
P
AR
TS
T
o
prepare
bare
aluminum
surface
for
intermediate
primer
.
Bonderite
M
-
CR
1
132
,
(formerly
the
Alodine
1
132
T
ouch
-
n
-
prep)
are
both
approved
for
small
touch
up
areas
,
generally
less
than
6
inches
square.)
Isopropyl
Alcohol
Commercially
A
vailable
T
o
clean
metal
surfaces
prior
to
bonding.
T
OOLING
No
specialized
tooling
is
required
to
complete
this
service
document.
REFERENCES
Beechcraft
Super
King
Air
B200GT
/
B200CGT
Fusion
Maintenance
Manual
Beechcraft
Super
King
Air
B300
/
B300C
Fusion
Maintenance
Manual
Beechcraft
Structural
Inspection
and
Repair
Manual
PUBLICA
TIONS
AFFECTED
None

### Page 3

Beechcraft
SER
VICE
LETTER
MANDA
T
OR
Y
MTL
-
27
-
07
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
main
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
copilot
seats.
•
For
all
Beechcraft
Model
B300
airplanes
,
refer
to
the
Beechcraft
Super
King
Air
B300
/
B300C
Fusion
Maintenance
Manual
,
Chapter
25
,
Pilot
and
Copilot
Seat
-
Removal
/
Installation.
•
For
all
Beechcraft
Model
B200
airplanes
,
refer
to
the
Beechcraft
Super
King
Air
B200GT
/
B200CGT
Fusion
Maintenance
Manual
,
chapter
25
,
Flight
Compartment
Seat
Removal
/
Installation.
3.
Remove
the
131A
TL
,
141A
TL
,
132A
TR
,
142A
TR
,
31
1CL
(B200
Model
Airplanes
)
,
and
31
1BL
(B300
Model
Airplanes)
Access
Panels.
(Refer
to
the
applicable
Beechcraft
Maintenance
Manual
,
Chapter
6
,
Airplane
Access
Panels
-
Description
and
Operation.)
4.
(Refer
to
Figure
1
,
Sheet
1)
Using
a
high
powered
flashlight
and
an
inspection
mirror
,
inspect
the
four
attaching
rivets
on
the
129
-
524126
-
001
1
Left
Pilot's
Rudder
Pushrod
as
follows:
NOTE:
Any
identified
soft
rivet
(no
marking)
regardless
of
rivet
location
and
/
or
left
and
right
pushrods
,
must
be
replaced
in
the
time
stated
within
the
compliance
section
•
No
mark
(alloy
code
A):
1
100
or
3003
pure
aluminum
•
Dimple
(alloy
code
AD)
21
17
aluminum
alloy
A.
If
any
of
the
four
rivets
do
not
have
the
dimple
marking
on
the
center
of
the
rivet
head
or
if
the
marking
can
not
be
determined
on
the
rivet
head
,
go
to
Step
4.
A.
(1).
(1)
Mark
all
rivets
without
a
dimpled
marking
on
the
center
of
the
rivet
head
with
an
indelible
marker
.
NOTE:
The
marking
of
the
129
-
524126
-
001
1
Left
Pilot's
Rudder
Pushrod
is
to
help
the
technician
remember
which
rivets
have
been
installed
incorrectly
into
the
129
-
524126
-
001
1
Left
Pilot's
Rudder
Pushrod.
MTL
-
27
-
07
July
25
,
2025
Page
3

### Page 4

MTL
-
27
-
07
Page
4
July
25
,
2025
Beechcraft
SER
VICE
LETTER
MANDA
T
OR
Y
MTL
-
27
-
07
B.
If
all
four
rivets
have
a
clear
dimple
marking
on
the
center
of
the
rivet
head
,
go
to
Step
5.
5.
Repeat
Step
4
for
the
right
129
-
524126
-
0013
Right
Pilot's
Rudder
Pushrod
,
the
129
-
524126
-
001
1
Left
Co
-
Pilot's
Rudder
Pushrod
,
and
the
129
-
524126
-
0013
Right
Co
-
Pilot's
Rudder
Pushrod.
6.
Depending
upon
the
inspection
of
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod
do
as
follows:
NOTE:
Any
identified
soft
rivet
(no
marking)
regardless
of
rivet
location
and
/
or
left
and
right
pushrods
,
must
be
replaced
in
the
time
stated
within
the
compliance
section
•
No
mark
(alloy
code
A):
1
100
or
3003
pure
aluminum
•
Dimple
(alloy
code
AD)
21
17
aluminum
alloy
A.
If
all
sixteen
rivets
for
the
129
-
524126
-
001
1
Left
and
129
-
524126
-
0013
Right
Pilot's
and
Co
-
Pilot's
Rudder
Pushrod's
has
a
dimple
marking
on
the
rivet
head
,
then
go
to
Step
13.
B.
Regardless
of
the
inspection
results
,
if
there
are
two
or
one
marked
rivet
on
the
same
rod
end
for
any
of
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrods
,
go
to
Step
7.
7.
Remove
the
marked
rivet(s)
from
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod
as
follows:
A.
(Refer
to
Figure
2
,
Sheet
1.)
Starting
from
the
pilot's
left
rudder
pushrod
,
remove
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod
as
follows:
(1)
Disconnect
the
electrical
connector
from
the
rudder
pedal
input
force
transducer
.
(2)
Remove
and
discard
the
two
MS24665
-
132
Cotter
Pins.
(3)
Remove
and
discard
the
two
MS17825
-
3
Nuts.
(4)
Remove
and
keep
the
two
bolts
and
washers
from
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod.
CAUTION:
Prior
to
the
removal
of
any
rivet
from
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod
,
the
pushrod
should
be
placed
in
a
clamping
device
so
that
the
pushrod
does
not
move
or
rotate
when
removing
the
marked
rivet.
Failure
to
secure
the
pushrod
may
oversize
the
hole
within
the
pushrod
assembly
.
B.
Remove
the
marked
rivet
from
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod.
(Refer
to
the
Beechcraft
Structural
Inspection
and
Repair
Manual
,
Chapter
20
,
Fastener
Installation
and
Removal.)
C.
Clean
out
the
drilled
hole
using
Isopropyl
Alcohol.
D.
Apply
Color
Chemical
Film
T
reatment
to
all
bare
aluminum.
E.
Install
a
MS20470AD4
-
12
Rivet
,
wet
with
Corrosion
Resistant
Primer
into
the
existing
drilled
hole.
(Refer
to
the
Beechcraft
Structural
Inspection
and
Repair
Manual
,
Chapter
20
,
Fastener
Installation
and
Removal.)
F
.
Repeat
Step
7.
A.
thru
7.
E.
for
any
additional
marked
rivet
on
the
removed
rudder
pushrod.
8.
(Refer
to
Figure
2
,
Sheet
1.)
Starting
from
the
pilot's
left
rudder
pushrod
,
install
the
129
-
524126
-
001
1
Left
Pilot's
Rudder
Pushrod:
NOTE:
The
installation
of
the
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod
is
the
same
for
all
of
the
rudder
pushrods.
A.
Install
the
129
-
524126
-
001
1
Left
Pilot's
Rudder
Pushrod
with
the
kept
bolts
and
washers.
B.
Install
a
MS17825
-
3
Nut
onto
each
end
of
the
129
-
524126
-
001
1
Left
Pilot's
Rudder
Pushrod.
C.
T
orque
the
two
MS17825
-
3
Nuts.
(Refer
to
the
Beechcraft
King
Air
Chapter
20
Standard
Practices
-
Airframe
,
Chapter
20
,
Bolt
Installation
and
T
orque
Application
-
Maintenance
Practices.)

### Page 5

Beechcraft
SER
VICE
LETTER
MANDA
T
OR
Y
MTL
-
27
-
07
D.
Install
a
MS24665
-
132
Cotter
Pin(s)
into
each
torque
MS17825
-
3
Nut(s).
E.
Connect
the
electrical
connector
to
the
rudder
pedal
input
force
transducer
.
F
.
Repeat
Step
9
for
the
three
remaining
129
-
524126
-
001
1
Left
or
129
-
524126
-
0013
Right
Pilot's
or
Co
-
Pilot's
Rudder
Pushrod.
9.
Remove
the
maintenance
warning
tags
and
connect
the
airplane
battery
.
10.
Do
a
full
swing
,
from
left
to
right
,
of
the
rudder
control
system
and
make
sure
that
each
primary
stop
is
touched.
1
1.
Do
the
Rudder
Pedal
Input
Forces
T
ransducer
Functional
T
est.
(Refer
to
the
applicable
Maintenance
Manual
,
Chapter
31
,
Rudder
Pedal
Input
Forces
T
ransducer
-
Adjustment
/
T
est.)
12.
Install
the
131A
TL
,
141A
TL
,
132A
TR
,
142A
TR
,
31
1CL
(B200
Model
Airplanes
)
,
and
31
1BL
(B300
Model
Airplanes)
Access
Panels.
(Refer
to
the
applicable
Beechcraft
Maintenance
Manual
,
Chapter
6
,
Airplane
Access
Panels
-
Description
and
Operation.)
13.
Install
the
pilot
and
copilot
seats.
•
For
all
Beechcraft
Model
B300
airplanes
,
refer
to
the
Beechcraft
Super
King
Air
B300
/
B300C
Fusion
Maintenance
Manual
,
Chapter
25
,
Pilot
and
Copilot
Seat
-
Removal
/
Installation.
•
For
all
Beechcraft
Model
B200
airplanes
,
refer
to
the
Beechcraft
Super
King
Air
B200GT
/
B200CGT
Fusion
Maintenance
Manual
,
Chapter
25
,
Flight
Compartment
Seat
Removal
/
Installation.
14.
Make
an
entry
in
the
airplane
logbook
that
states
compliance
and
method
of
compliance
with
this
service
document.
NOTE:
T
extron
A
viation
recommends
that
compliance
with
all
service
documents
is
reported
to
a
maintenance
tracking
system
provider
.
•
Complete
a
record
of
compliance.
(Maintenance
T
ransaction
Report
,
Log
Book
Entry
,
or
other
record
of
compliance.)
•
Put
a
copy
of
the
completed
record
of
compliance
in
the
airplane
logbook.
•
Send
a
copy
of
the
completed
record
of
compliance
to
the
maintenance
tracking
system
provider
used.
MTL
-
27
-
07
July
25
,
2025
Page
5

### Page 6 (OCR)

Beechcraft  Hawker
Beechcraft  SERVICE LETTER  TEXTRON ÀVIATION  Cessna
MANDATORY  MTL-27-07
E78481
0000001°
Rudder Pedal Pushrod
• (Reference)
Rivets to Inspect
Rivets to Inspect  MS20740AD4-12
MS20740AD4-12  Rivet
Rivet  (As Required, 2 Total)
(As Required, 2 Total)
DETAIL A
(View Looking Down at Rudder Pushrod)
NOTE: The Pilot's and Co-Pilot's rudder pushrods are typical to each other.
Figure 1. Rivet Pushrod Inspection (Sheet 1)
MTL-27-07
Page 6  July 25, 2025

### Page 7 (OCR)

Beechcrafi  Hawker
Beechcraft  SERVICE LETTER  TEXTRON ÀVIATION  Cessna
MANDATORY  MTL-27-07
E78482
00001
Rudder Pedal
(Reference)
MS24665-132
Cotter Pin
(As Required, 2 Total)
MS17825-3
Nut
-(As Required, 2 Total)
Washer
(Reference)
Connector
Bolt  (Reference)
(Reference)
129-524126-0011 (Left)
Force Transducer
129-524126-0013 (Right)
Rudder Pedal Pushrod  (Reference)
(Reference)
DETAIL A
Figure 2. Rudder Pushrod Installation (Sheet 1)
MTL-27-07
July 25, 2025  Page 7

### Page 8

MTL
-
27
-
07
Page
8
July
25
,
2025
Beechcraft
SER
VICE
LETTER
MANDA
T
OR
Y
MTL
-
27
-
07
MA
TERIAL
INFORMA
TION
The
parts
below
may
be
required
to
complete
this
service
letter
.
NEW
P
/
N
QUAN-
TITY
KEY
WORD
OLD
P
/
N
INSTRUCTIONS
/
DISPOSITION
MS20470AD4
-
12
4
T
otal
Per
Pushrod
(As
Required)
Rivet
V
arious
Discard
old
,
Install
new
.
MS24665
-
132
2
T
otal
Per
Pushrod
(As
Required)
Cotter
Pin
Same
Discard
old
,
Install
new
.
MS17825
-
3
2
T
otal
Per
Pushrod
(As
Required)
Nut
Same
Discard
old
,
Install
new
.
*
Please
contact
your
Regional
T
extron
A
viation
Parts
Distribution
Customer
Support
T
eam
for
current
cost
and
availability
of
parts
listed
in
this
service
document.
Phone
at
1
-
800
-
835
-
4000
(Domestic)
or
1
-
316
-
517
-
5603
(International).
For
more
information
,
please
visit
the
T
APD
Support
&
Aftermarket
Account
Management
website
at
https:
/
/
ww2.txtav
.com
/
Parts.
Based
on
availability
and
lead
times
,
parts
may
require
advanced
scheduling.

### Page 9

Beechcraft
OWNER
ADVISOR
Y
MTL
-
27
-
07
TITLE
FLIGHT
CONTROLS
-
PILOT
AND
COPILOT
RUDDER
PEDAL
PUSHROD
LINKAGE
INSPECTION
T
O:
Beechcraft
Model
B200GT
,
B200CGT
,
B300
,
and
B300C
Aircraft
Owner
REASON
During
installation
of
the
rudder
pushrod
rod
end
the
incorrect
type
of
rivet
that
attaches
the
rod
end
may
have
been
installed.
If
the
incorrect
rivet
was
installed
this
could
cause
the
rudder
pushrod
tube
to
separate
from
the
rod
end.
Failure
to
comply
can
result
in
loss
of
rudder
control
which
can
result
in
loss
of
control
of
the
airplane
during
flight
or
ground
operations.
COMPLIANCE
MANDA
T
OR
Y
.
This
service
document
must
be
accomplished
by
airplanes
that
have
the
DFDR
installed.
NOTE:
Regardless
if
there
are
two
adjacent
or
one
marked
rivet
on
the
same
rod
end
all
marked
rivet(s)
needs
to
be
replaced
at
the
same
time
that
is
stated
within
the
compliance
section.
NOTE:
If
any
of
the
left
and
/
or
right
rudder
pushrods
have
two
adjacent
soft
rivets
on
any
one
of
the
pushrod
ends
,
then
all
of
the
soft
rivets
on
any
rod
ends
of
the
left
and
/
or
right
pushrod
ends
,
the
soft
rivets
must
be
replaced.
Criteria
Compliance
T
ime
Inspection
Within
20
flight
hours
or
30
days
from
the
service
document
date
,
which
ever
occurs
first.
If
2
soft
rivets
are
found
adjacent
to
each
other
on
the
same
rod
end
for
one
pushrod.
Before
next
flight.
If
1
soft
rivet
and
1
hard
rivet
are
installed
on
any
of
the
4
rod
ends.
Within
200
flight
hours
or
12
month
inspection
,
whichever
occurs
first.
LABOR
HOURS
WORK
PHASE
LABOR
-
HOURS
Modification
16.0
MA
TERIAL
A
V
AILABILITY
P
ART
NUMBER
A
V
AILABILITY
COST
MS20470AD4
-
12
*
*
MS24665
-
132
*
*
MS17825
-
3
*
*
*
Please
contact
your
Regional
T
extron
A
viation
Parts
Distribution
Customer
Support
T
eam
for
current
cost
and
availability
of
parts
listed
in
this
service
document.
Phone
at
1
-
800
-
835
-
4000
(Domestic)
or
1
-
316
-
517
-
5603
(International).
MTL
-
27
-
07
July
25
,
2025
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
©
2025

### Page 10

MTL
-
27
-
07
Page
2
July
25
,
2025
Beechcraft
OWNER
ADVISOR
Y
MTL
-
27
-
07
For
more
information
,
please
visit
the
T
APD
Support
&
Aftermarket
Account
Management
website
at
https:
/
/
ww2.txtav
.com
/
Parts.
Based
on
availability
and
lead
times
,
parts
may
require
advanced
scheduling.
W
ARRANTY
This
service
document
is
mandatory
.
Eligible
airplanes
may
qualify
for
parts
and
labor
coverage
to
the
extent
noted
in
the
Labor
Hours
and
Material
A
vailability
sections
of
this
document.
Eligibility:
Airplanes
identified
within
the
serial
number
ef
fectivity
of
this
service
document
must
have
active
Airframe
warranty
coverage
on
the
original
issue
date
of
this
document
and
the
coverage
must
be
active
on
the
day
the
work
is
accomplished.
Parts
Coverage:
T
extron
A
viation
-
owned
and
T
extron
A
viation
-
authorized
Service
Facilities
,
operators
,
or
other
maintenance
facilities
may
submit
a
claim
for
the
parts
required
to
accomplish
this
service
document
as
defined
in
the
Material
A
vailability
section
of
this
document.
Labor
Coverage:
T
extron
A
viation
-
owned
and
T
extron
A
viation
-
authorized
Service
Facilities
rated
to
perform
maintenance
on
the
specific
model
of
Beechcraft
Aircraft
may
submit
a
claim
for
the
labor
necessary
to
accomplish
this
service
document
as
defined
in
the
Labor
Hours
section
of
this
document.
Credit
Application:
After
this
service
document
has
been
accomplished
,
a
claim
must
be
submitted
to
T
extron
A
viation
within
30
days
of
the
service
document
completion.
Claims
for
compliance
of
this
service
document
are
to
be
filed
as
a
W4
type
claim.
Please
submit
your
claim
form
online
at
ww2.txtav
.com
/
Parts
or
email
the
completed
T
extron
A
viation
Claim
Form
to
warranty@txtav
.com
.
If
submitted
on
-
line
a
Return
Authorization
will
be
provided.
If
a
paper
claim
is
submitted
your
claim
will
be
entered
into
the
system
and
a
Return
Authorization
will
be
sent
to
you.
The
Return
Authorization
must
accompany
any
required
return
parts
(see
Material
A
vailability
)
,
to
the
point
of
purchase.
Parts
to
be
returned
to
T
extron
A
viation
should
be
forwarded
to:
TEXTRON
A
VIA
TION
P
AR
TS
DISTRIBUTION
W
ARRANTY
ADMINISTRA
TION
BLDG
P43
DOCK
R5
7123
SW
BL
VD
Wichita
,
KS
67215
Expiration:
July
31
,
2027
(after
this
date
the
owner
/
operator
assumes
the
responsibility
for
compliance
costs)
T
extron
A
viation
reserves
the
right
to
void
continued
airplane
warranty
coverage
for
the
parts
af
fected
by
this
service
document
until
the
service
document
is
accomplished.
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
support.txtav
.com
to
register
.

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.