# Airbus Service Bulletin 235-53-0070C

Copy: No revision named ("SB235-53-0070-C"), 41 pages: PDF https://openairdocs.org/files/sha256/fd/85/fd85f7a2dd6e18a560654dfc8613c9fc93f26ecfd24d00022dec1d616644180c; text https://openairdocs.org/service-documents/airbus/235-53-0070c/file/fd85f7a2dd6e.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2023-1999, the docket of AD 2023-25-11. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: 235-53-0070C
- Page: https://openairdocs.org/service-documents/airbus/235-53-0070c

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2023-25-11](https://openairdocs.org/ad/2023-25-11.md), effective Feb 7, 2024: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/235-53-0070c/proposed.md).

## Text (41 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2023-1999, the docket of AD 2023-25-11. Not covered by OpenAirDocs’ CC0 dedication. 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

SER
VICE
BULLETIN
AIRBUS
DEFENCE
AND
SP
ACE
ENGINEERING
SUPPOR
T
-
SER
VICE
ENGINEERING
Autovía
A-4,
km
528,5.
San
Pablo
North.
41020
Seville
SP
AIN
T
el
:
(34)
954594169
MANDA
T
OR
Y
MANDA
T
OR
Y
MANDA
T
OR
Y
A
T
A
SYSTEM:
53
TITLE:
FUSELAGE.
REAR
FUSELAGE.
REINFORCEMENT
OF
THE
STRUCTURE
BETWEEN
FRAMES
FR43
AND
FR45.
DESIGN
CHANGE
No.:
DC1
1332-E
This
document
contains
AIRBUS
DEFENCE
AND
SP
ACE
PROPRIET
AR
Y
INFORMA
TION
and
shall
at
all
times
remain
the
property
of
AIRBUS
DEFENCE
AND
SP
ACE;
no
intellectual
property
right
or
licence
is
granted
by
AIRBUS
DEFENCE
AND
SP
ACE
in
connection
with
any
information
contained
in
it.
It
is
delivered
on
the
express
condition
that
said
document
and
the
information
contained
in
it
shall
be
treated
as
confidential,
shall
not
be
used
for
any
purpose
other
than
that
for
which
it
is
hereby
delivered.
It
shall
not
be
disclosed
in
whole
or
in
part
to
third
parties
and
shall
not
be
duplicated
in
any
manner
(except
for
the
purposes
of
performing
the
tasks
described
hereunder
and
provided
that
any
recipient
of
such
document
shall
comply
with
the
conditions
herein),
without
AIRBUS
DEFENCE
AND
SP
ACE
prior
written
consent.
1.
PLANNING
INFORMA
TION
A.
EFFECTIVITY
(1)
Models
CN-235
CN-235-200
CN-235-300
(2)
Ef
fectivity
C007
C012
C018
C030
C042
C130
C135
C139
C143
C145
C166
C169
C171
C176
C177
C182
C186
(3)
Ef
fectivity
by
version
The
V
ersion/MSN
relationship
is
provided
for
information
only
and
is
correct
at
the
time
of
issue
in
accordance
with
the
information
available
to
AIRBUS
DEFENCE
AND
SP
ACE.
Any
future
changes
resulting
from
transfer
of
an
aircraft
from
one
operator
to
another
will
not
be
reflected
in
this
list
unless
the
Service
Bulletin
is
revised
for
another
reason.
VERSION
MSN
AE01
C135
AE02
C139
C143
C145
IB01
C007
C012
IB02
C018
C030
L302
C130
L303
C176
C177
C182
C186
QC02
C042
SM01
C166
C169
C171
(4)
Configuration
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
1
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 2

SER
VICE
BULLETIN
MSN
CONFIGURA
TION
C007
C012
C018
C030
C042
C130
C135
C139
C145
C166
C169
C171
C176
C177
C182
C186
001
C143
002
(5)
Configuration
definition
**CONF
001
CONF_001
is
only
applicable
to
aircraft:
AE01,
AE02
(C139,C145),
IB01,
IB02,
L302,
L303,
QC02,
SM01.
**CONF
002
CONF_002
is
only
applicable
to
aircraft:
AE02
(C-143).
The
permanent
repair
referenced
in
ANNEX
I
was
done
on
this
aircraft.
Thus,
this
SB
is
done
and
no
more
action
is
necessary
.
Refer
to
section
APPENDICES
.
(6)
Material
Ef
fectivity
CONF
001
MA
TERIAL
QTY
PER
A/C
NOTE
Kit
SB235530070K01
1
Consumable
CMLS01
As
required
B.
CONCURRENT
REQUIREMENTS
CONF
001
None.
C.
REASON
(1)
History
Cracks
were
found
in
stringers
STGR0A
and
STGR0A
’,
between
frames
FR43
and
FR44,
on
some
aircraft
CN-235.
A
study
was
done
on
the
analysis
of
fatigue
in
the
af
fected
area
to
do
the
necessary
modifications
and
to
prevent
cracks.
(2)
Objective/Action
T
o
make
the
af
fected
area
stronger
to
prevent
cracks.
(3)
Advantages
T
o
prevent
cracks
in
the
af
fected
area.
(4)
Operational/Maintenance
Consequences
None.
D.
DESCRIPTION
T
o
accomplish
this
Service
Bulletin
it
is
necessary
to:
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
2
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 3

SER
VICE
BULLETIN
CONF
001
T
ask
C530070-831-801-000
-
Modification
-
Configuration
of
the
W
ork
Area.
-
Removal.
-
Installation.
E.
COMPLIANCE
(1)
Classification
MANDA
T
OR
Y
:
After
the
revision
of
Airworthiness
Directive
(AD)
2020-0159
published
by
the
European
A
viation
Safety
Agency
(EASA),
it
is
possible
that
this
Service
Bulletin
will
be
mandatory
.
It
is
possible
that
the
AD
will
confirm
the
thresholds
and/or
intervals
and/or
date
given
before,
but
you
must
refer
to
the
AD
to
confirm
the
estimated
accomplishment
timescale.
(2)
Accomplishment
T
imescales
5000FC
or
9
months,
that
which
comes
last.
F
.
APPROV
AL
This
issue
is
a
translation
of
SB-235-53-0070-C.
In
case
of
any
disagreement,
reference
should
be
made
to
the
Spanish
original
issue,
which
has
approved
under
the
authority
of
the
DOA
No.
EASA.21J.032.
G.
MANPOWER
The
manpower
estimates
given
in
this
Service
Bulletin
are
based
on
the
direct
labor
cost
to
do
the
work.
These
estimates
assume
that
the
work
will
be
done
by
experienced
personnel,
and
may
need
to
be
revised
upwards
to
suit
operator
’
s
circumstances.
The
estimates
do
not
include
the
time
to
prepare,
plan
or
inspect
the
work.
Manufacture
and
procurement
of
parts
and
tools,
drying
times
for
paints,
sealants,
etc.,
and
general
administration
work
are
also
not
included.
CONF
001
T
ask
C530070-831-801-000
-
MODIFICA
TION
Manhours
Num.
Persons
On
Aircraft
Configuration
of
the
W
ork
Area.
2.00
1
Removal.
3.00
1
Installation.
9.00
1
T
est
T
ests.
1.00
1
T
OT
AL
MANHOURS
15.00
ELAPSED
TIME
(HOURS)
15.00
H.
WEIGHT
AND
BALANCE
CONF
001
(1)
V
ariation
of
the
Standard
Basic
Empty
W
eight
(SBEW).
Kit
SB235530070K01:
W
eight
=
+
2,803
Kg
(2)
V
ariation
of
the
momentum
in
relation
to
the
reference
plane.
Kit
SB235530070K01:
Momentum
=
+
52,909
Kg·m
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
3
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 4

SER
VICE
BULLETIN
I.
ELECTRICAL
LOAD
DA
T
A
(1)
Direct
Current
Load
Changes
CONF
001
No
changes
(2)
Alternating
Current
Load
Changes
CONF
001
No
changes
J.
REFERENCES
CONF
001
Aircraft
Maintenance
Manual
AMM
20-21-00
AMM
20-27-00
AMM
20-28-00
AMM
20-38-00
AMM
20-50-00
AMM
52-32-23
Structural
Repair
Manual
SRM
51-24-00
SRM
51-40-00
SRM
51-41-10
K.
PUBLICA
TION
AFFECTED
CONF
001
Structural
Repair
Manual
SRM
53-31-1
1
V
ariation
04
of
Issue
R
in
the
List
of
Airworthiness
Limitations
CN-235,
DT
-86-3001
V
ariation
04
of
Issue
A
of
Airworthiness
Limitations
CN-235-300MP
,
DT
-06-3009
L.
INTERCHANGEABILITY/MIXABILITY
CONF
001
DESCRIPTION
OLD
P
AR
T
N°
NEW
P
AR
T
N°
INT
MIXABILITY
SEE
NOTE
SUPPOR
T
35-231
13-0001
95-A1472-0001
03
N/A
FORMER
35-23136-0903
95-A1473-0101
03
N/A
FORMER
35-23136-0904
95-A1473-0102
03
N/A
FORMER
35-23008-0101
95-A1473-0301
03
N/A
FORMER
35-23008-0102
95-A1473-0302
03
N/A
FORMER
35-23008-9501
95-A1473-0201
03
N/A
FORMER
35-23008-9502
95-A1473-0202
03
N/A
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
4
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 5

SER
VICE
BULLETIN
NOTE:
INT
03
-
Not
interchangeable.
M.
SP
ARES
None
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
5
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 6

SER
VICE
BULLETIN
This
Page
Intentionally
Left
Blank.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
6
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 7

SER
VICE
BULLETIN
2.
MA
TERIAL
INFORMA
TION
A.
MA
TERIAL
-
PRICE
AND
A
V
AILABILITY
(1)
Procurement
Address
Operators
with
aircraft
show
in
the
ef
fectivity
of
this
Service
Bulletin
should
send
a
purchase
order
to
AIRBUS
DEFENCE
AND
SP
ACE.
Quote
the
number
of
the
Service
Bulletin.
The
address
is:
AIRBUS
SER
VICES
-
MA
TERIAL
SUPPOR
T
A
vda.
de
Aragón,
404
28022
MADRID
SP
AIN
Fax:
+34
91
585
31
27
(2)
Price
and
A
vailability
Sales
terms
must
be
agreed
between
the
Operator
and
AIRBUS
in
accordance
with
the
established
procedure.
B.
INDUSTR
Y
SUPPORT
INFORMA
TION
None
C.
LIST
OF
COMPONENTS
CONF
001
Kit
SB235530070K01
ITEM
NEW
P
AR
T
N°
QTY
(UM)
KEYWORD
ITEM
OLD
P
AR
T
N°
INT
SEE
NOTE
ITEM
32
95-A1472-0001
1
SUPPOR
T
ITEM
31
35-231
13-0001
03
ITEM
34
95-A1473-0101
1
FORMER
ITEM
33
35-23136-0903
03
ITEM
36
95-A1473-0102
1
FORMER
ITEM
35
35-23136-0904
03
ITEM
38
95-A1473-0301
1
FORMER
ITEM
37
35-23008-0101
03
ITEM
40
95-A1473-0302
1
FORMER
ITEM
39
35-23008-0102
03
ITEM
42
95-A1473-0201
1
FORMER
ITEM
41
35-23008-9501
03
ITEM
44
95-A1473-0202
1
FORMER
ITEM
43
35-23008-9502
03
ITEM
46
95-23138-0101
1
FITTING
ITEM
48
95-23138-0102
1
FITTING
ITEM
54
95-23137-0101
1
FITTING
ITEM
56
95-23137-0102
1
FITTING
ITEM
60
95-A1500-0101
1
RADIUS
GUARDS
ITEM
61
95-A1500-0102
1
RADIUS
GUARDS
ITEM
62
95-A1501-0101
1
RADIUS
GUARDS
ITEM
63
95-A1501-0102
1
RADIUS
GUARDS
ITEM
64
95-A1502-0101
1
RADIUS
GUARDS
ITEM
65
95-A1502-0102
1
RADIUS
GUARDS
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
7
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 8

SER
VICE
BULLETIN
ITEM
66
95-A1503-0101
1
RADIUS
GUARDS
ITEM
67
95-A1503-0102
1
RADIUS
GUARDS
ITEM
68
95-A1504-0101
4
RADIUS
GUARDS
ITEM
69
95-A1505-0101
4
RADIUS
GUARDS
ITEM
301
EN61
15K3-6
4
HI-LITE
RIVET
ITEM
302
EN61
15K3-4
1
HI-LITE
RIVET
ITEM
303
EN61
15K3-5
9
HI-LITE
RIVET
ITEM
304
EN61
15K3-7
22
HI-LITE
RIVET
ITEM
305
MS20470E5-6
86
RIVET
ITEM
306
MS20470E5-7
76
RIVET
ITEM
307
EN61
15K2-3
4
HI-LITE
RIVET
ITEM
308
ASNA2536-2
4
HI-LITE
NUT
ITEM
309
EN61
15K3-3
4
HI-LITE
RIVET
ITEM
310
MS20426AD3-4
4
RIVET
ITEM
31
1
ASNA2536-3
56
HI-LITE
NUT
ITEM
312
EN61
15K3-8
12
HI-LITE
RIVET
ITEM
313
EN61
15K3-9
4
HI-LITE
RIVET
ITEM
320
MS21061L3
1
NUT
ITEM
341
NAS1097KE5-7
4
RIVET
NOTE:
INT
03
-
Not
interchangeable.
D.
LIST
OF
MA
TERIALS
-
OPERA
T
OR
SUPPLIED
(1)
Consumable
materials
CONF
001
Consumable
CMLS01
ITEM
DESCRIPTION
REFERENCE
CML
QTY
PER
AIRCRAFT
SEE
NOTE
V
ARNISH
MA
T
.
No.
Z-12.560
A/R
SEALANT
MA
T
.
No.
Z-16.171
A/R
SEALANT
MA
T
.
No.
Z-16.176
A/R
SEALANT
MA
T
.
No.
Z-16.177
A/R
NOTE:
T
o
accomplish
this
Service
Bulletin
it
is
also
necessary
to
use
the
consumable
materials
listed
in
the
reference
procedures.
(2)
Components
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
8
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 9

SER
VICE
BULLETIN
CONF
001
NOTE:
Those
given
in
the
reference
procedures.
(3)
Equipment
CONF
001
NOTE:
Those
given
in
the
reference
procedures.
E.
P
ARTS
T
O
BE
RE-IDENTIFIED
BY
OPERA
T
OR
CONF
001
None
F
.
T
OOLING
(1)
T
ooling
Price
and
A
vailability
None
(2)
Standard
T
ools
CONF
001
NOTE:
Those
given
in
the
reference
procedures.
(3)
Special
T
ools
CONF
001
None
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
9
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 10

SER
VICE
BULLETIN
This
Page
Intentionally
Left
Blank.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
10
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 11

SER
VICE
BULLETIN
3.
ACCOMPLISHMENT
INSTRUCTIONS
T
ask
C530070-831-801-000
-
Modification
W
ARNING:
MAKE
SURE
THA
T
YOU
OBEY
ALL
THE
W
ARNING
INDICA
TIONS
INCLUDED
IN
THE
REFERENCE
PROCEDURES.
W
ARNING:
BE
CAREFUL
WHEN
YOU
USE
CONSUMABLE
MA
TERIALS.
MAKE
SURE
THA
T
YOU
OBEY
THE
INSTRUCTIONS
FROM
THE
PRODUCT
MANUF
ACTURER
AND
THE
LOCAL
SPECIFICA
TIONS.
CAUTION:
DISCONNECT
ALL
THE
ENERGY
SUPPLIES.
NOTE:
The
discarded
items
must
be
managed
based
on
the
operator's
criteria.
T
ask
Associated
Data
CONF
001
Zone
260
810
Modified
FIN
None
Access
Rear
Fuselage
FR43
-
FR45
V
entral
door
FR39
-
FR46
Manpower
T
OT
AL
MANHOURS
15.00
ELAPSED
TIME
(HOURS)
15.00
A.
GENERAL
CONF
001
(1)
Subtask
C530070-834-001-001
-
W
ork
Breakdown.
Manpower
Resources
Skills
Non
specific
On
aircraft:
(a)
Put
warning
notices
in
position.
(b)
Put
the
aircraft
in
the
safe
condition
for
maintenance
tasks.
(c)
Get
access
to
the
work
area.
(d)
Remove
the
V
entral
Door
Actuator
.
(e)
Remove
the
parts
of
the
structure.
(f)
Install
new
structural
items.
(g)
Do
tests.
(h)
Remove
the
warning
notices.
(i)
Record
the
accomplishment.
CONF
001
(1)
Subtask
C530070-910-001-001
-
Standard
Practices.
Manpower
Resources
Skills
Non
specific
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
1
1
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 12

SER
VICE
BULLETIN
References
Aircraft
Maintenance
Manual
AMM
20-21-00
AMM
20-27-00
AMM
20-28-00
AMM
20-38-00
AMM
20-50-00
Structural
Repair
Manual
SRM
51-24-00
SRM
51-40-00
(a)
Standard
T
orques.
Refer
to
Aircraft
Maintenance
Manual
AMM
20-21-00
.
(b)
Electrical
Wiring
and
Wire
Harnesses.
Refer
to
Aircraft
Maintenance
Manual
AMM
20-27-00
.
(c)
Electrical
Bonding
-
General.
Refer
to
Aircraft
Maintenance
Manual
AMM
20-28-00
.
(d)
Sealant
Application.
Refer
to
Aircraft
Maintenance
Manual
AMM
20-38-00
.
(e)
Surface
T
reatment.
Refer
to
Aircraft
Maintenance
Manual
AMM
20-50-00
.
(f)
Sealing.
Refer
to
Structural
Repair
Manual
SRM
51-24-00
.
(g)
Fasteners.
Refer
to
Structural
Repair
Manual
SRM
51-40-00
.
B.
PREP
ARA
TION
CONF
001
(1)
Subtask
C530070-941-001-001
-
Job
Set-up.
Manpower
Resources
Skills
Non
specific
(a)
Put
warning
notices
in
position
to
show
personnel
that
maintenance
tasks
are
in
progress.
(b)
Prepare
the
aircraft
for
the
tasks
and
obey
all
the
safety
precautions.
(c)
Disconnect
all
the
energy
supplies.
Make
sure
that
all
the
related
electrical
circuits
are
isolated.
Put
warning
notices
in
position
to
prevent
the
supply
of
electrical
power
to
the
aircraft.
(d)
Put
warning
notices
in
the
correct
position
to
prevent
accidental
operation
of
a
control
or
system.
(e)
Make
sure
that
you
obey
the
Necessary
Conditions
and
the
Safety
Conditions
given
in
the
reference
procedures.
(f)
Open,
safety
clip
and
tag
the
circuit
breakers
given
in
the
reference
procedures.
(g)
Prepare
the
aircraft
access
panels
and
find
the
area
where
the
Service
Bulletin
will
apply
.
(h)
Prepare
the
consumable
material
that
is
necessary
to
do
the
work.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
12
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 13

SER
VICE
BULLETIN
C.
PROCEDURE
CONF
001
NOTE:
The
item
numbers
referred
to
in
this
section
correspond
to
those
given
in
the
kit
and
in
the
dif
ferent
figures.
NOTE:
Do
the
surface
treatment
standard
practice
on
the
drill
holes
that
you
do.
NOTE:
All
the
dimensions
shown
in
this
document
are
in
millimeters,
unless
a
dif
ferent
unit
of
measurement
is
specified.
(1)
Subtask
C530070-840-001-001
-
Configuration
of
the
W
ork
Area.
W
ork
Zones
and
Access
Panels
Zone
Access/W
ork
location
260
Rear
Fuselage
FR43
-
FR45
810
V
entral
door
FR39
-
FR46
Manpower
Resources
Manhours
2.00
Minimum
number
of
person
1
Subtask
elapsed
time
2.00
Skills
Mechanical
Material
necessary
to
do
the
job
Kit
SB235530070K01
ITEM
NEW
P
AR
T
N°
QTY
(UM)
KEYWORD
ITEM
310
MS20426AD3-4
4.00
RIVET
ITEM
320
MS21061L3
1.00
NUT
Consumable
CMLS01
ITEM
DESCRIPTION
REFERENCE
CML
QTY
PER
AIRCRAFT
V
ARNISH
MA
T
.
No.
Z-12.560
A/R
SEALANT
MA
T
.
No.
Z-16.171
A/R
SEALANT
MA
T
.
No.
Z-16.176
A/R
SEALANT
MA
T
.
No.
Z-16.177
A/R
References
Structural
Repair
Manual
SRM
51-41-10
Figure
1
Sheet
01
-
Removal
and
Configuration
of
the
W
ork
Area.
Sheet
03
-
Removal
and
Configuration
of
the
W
ork
Area.
Sheet
04
-
Removal
and
Configuration
of
the
W
ork
Area.
NOTE:
Obey
the
minimum
distance
between
the
drill
holes
and
between
the
drill
holes
and
the
edges.
Refer
to
Structural
Repair
Manual
SRM
51-41-10
.
(a)
On
frame
FR44,
change
the
installation
of
the
clamp
(71):
Refer
to
FIG.
1
Sheet
01
.
Refer
to
FIG.
1
Sheet
03
.
Refer
to
FIG.
1
Sheet
04
.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
13
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 14

SER
VICE
BULLETIN
1
Remove
and
keep
the
clamp
(71)
together
with
the
ground
plate
(72).
T
o
do
this,
remove
and
keep
the
screw
(321)
and
the
washer
(322).
1
CLAMP
MS21919WDG12
ITEM
71
Retain
1
GROUND
PLA
TE
CAN67320-3ADL
ITEM
72
Retain
1
BOL
T
AN3C4A
ITEM
321
Retain
1
W
ASHER
NAS1
149D0363H
or
AN960D10
ITEM
322
Retain
2
Remove
and
discard
the
nut
(320).
T
o
do
this,
remove
and
discard
the
rivets
shown
in
the
figure.
1
NUT
MS21061L3
ITEM
320
Discard
Fill
the
drill
holes
shown
in
the
figure.
T
o
do
this,
install
2
rivets
(310).
2
RIVET
MS20426AD3-4
ITEM
310
W
et
install
the
rivets
with
sealant:
SEALANT
MA
T
.
No.
Z-16.171
A/R
If
it
is
not
possible
to
fill
the
drill
holes
with
rivets
(310),
seal
them.
T
o
do
this,
apply:
SEALANT
MA
T
.
No.
Z-16.177
A/R
Seal
the
attaching
drill
hole
of
the
clamp
(71).
T
o
do
this,
apply:
SEALANT
MA
T
.
No.
Z-16.177
A/R
3
Do
the
drill
hole
in
frame
FR44
to
attach
the
clamp
(71)
in
the
new
position.
T
o
do
this:
-
Put
the
clamp
(71)
in
position
as
shown
in
the
figure.
-
Use
the
clamp
(71)
as
a
template
to
do
the
drill
hole
in
the
structure.
-
Remove
the
clamp
(71).
-
Drill
to
the
final
diameter
and
remove
the
burrs.
4
Install
1
nut
(320)
in
the
new
position.
T
o
do
this:
-
Put
the
nut
(320)
in
the
position
shown
in
the
figure
and
align
it
with
the
drill
hole.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
14
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 15

SER
VICE
BULLETIN
-
Use
the
nut
(320)
as
a
template
to
do
the
drill
holes
in
the
structure.
-
Remove
the
nut
(320).
-
Drill
to
the
final
diameter
and
countersink
the
drill
holes.
Remove
the
burrs.
-
Attach
the
nut
(320)
with
2
rivets
(310).
2
RIVET
MS20426AD3-4
ITEM
310
1
NUT
MS21061L3
ITEM
320
5
Install
the
clamp
(71)
and
the
ground
plate
(72)
that
you
kept
before.
T
o
do
this,
attach
them
with
the
screw
(321)
and
the
washer
(322)
that
you
kept
before.
1
CLAMP
MS21919WDG12
ITEM
71
Retained
at
removal
1
GROUND
PLA
TE
CAN67320-3ADL
ITEM
72
Retained
at
removal
1
BOL
T
AN3C4A
ITEM
321
Retained
at
removal
1
W
ASHER
NAS1
149D0363H
or
AN960D10
ITEM
322
Retained
at
removal
Apply
on
the
electrical
contact
point:
SEALANT
MA
T
.
No.
Z-16.176
A/R
V
ARNISH
MA
T
.
No.
Z-12.560
A/R
(2)
Subtask
C530070-020-001-001
-
Removal.
W
ork
Zones
and
Access
Panels
Zone
Access/W
ork
location
260
Rear
Fuselage
FR43
-
FR45
810
V
entral
door
FR39
-
FR46
Manpower
Resources
Manhours
3.00
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
15
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 16

SER
VICE
BULLETIN
Minimum
number
of
person
1
Subtask
elapsed
time
3.00
Skills
Mechanical
Material
necessary
to
do
the
job
Kit
SB235530070K01
ITEM
NEW
P
AR
T
N°
QTY
(UM)
KEYWORD
ITEM
341
NAS1097KE5-7
4.00
RIVET
Consumable
CMLS01
ITEM
DESCRIPTION
REFERENCE
CML
QTY
PER
AIRCRAFT
SEALANT
MA
T
.
No.
Z-16.171
A/R
SEALANT
MA
T
.
No.
Z-16.177
A/R
References
Aircraft
Maintenance
Manual
AMM
52-32-23
Figure
1
Sheet
01
-
Removal
and
Configuration
of
the
W
ork
Area.
Sheet
02
-
Removal
and
Configuration
of
the
W
ork
Area.
Sheet
03
-
Removal
and
Configuration
of
the
W
ork
Area.
CAUTION:
BE
VER
Y
CAREFUL
WHEN
YOU
REMOVE
THE
RIVETS.
DO
NOT
MAKE
THE
DRILL
HOLES
LARGER
OR
OV
AL.
(a)
Remove
and
keep
the
V
entral
Door
Actuator
.
Refer
to
Aircraft
Maintenance
Manual
AMM
52-32-23
.
(b)
On
frame
FR43,
remove
and
discard
the
support
(31).
T
o
do
this,
remove
and
discard
the
rivets
shown
in
the
figure.
Refer
to
FIG.
1
Sheet
01
.
1
SUPPOR
T
35-231
13-0001
ITEM
31
Discard
Fill
the
drill
holes
shown
in
the
figure.
T
o
do
this,
countersink
the
drill
holes
and
install
4
rivets
(341).
4
RIVET
NAS1097KE5-7
ITEM
341
W
et
install
the
rivets
with
sealant:
SEALANT
MA
T
.
No.
Z-16.171
A/R
If
it
is
not
possible
to
fill
the
drill
holes
with
rivets
(341),
seal
them.
T
o
do
this,
apply:
SEALANT
MA
T
.
No.
Z-16.177
A/R
(c)
Between
frames
FR43
and
FR44,
on
stringers
STGR0A
and
STGR0A
’,
remove
and
discard
the
angles
(33)
and
(35).
T
o
do
this,
remove
and
discard
the
rivets
shown
in
the
figure.
Refer
to
FIG.
1
Sheet
01
.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
16
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 17

SER
VICE
BULLETIN
Refer
to
FIG.
1
Sheet
02
.
1
ANGLE
35-23136-0903
ITEM
33
Discard
1
ANGLE
35-23136-0904
ITEM
35
Discard
(d)
Between
frames
FR43
and
FR44,
on
stringers
STGR1
and
STGR1’,
remove
and
discard
the
angles
(37)
and
(39).
T
o
do
this,
remove
and
discard
the
rivets
shown
in
the
figure.
Refer
to
FIG.
1
Sheet
01
.
Refer
to
FIG.
1
Sheet
02
.
1
ANGLE
35-23008-0101
ITEM
37
Discard
1
ANGLE
35-23008-0102
ITEM
39
Discard
(e)
On
frame
FR44
and
stringers
STGR0A
and
STGR0A
’,
remove
and
discard
the
angles
(41)
and
(43).
T
o
do
this,
remove
and
discard
the
rivets
shown
in
the
figure.
Refer
to
FIG.
1
Sheet
01
.
Refer
to
FIG.
1
Sheet
03
.
1
ANGLE
35-23008-9501
ITEM
41
Discard
1
ANGLE
35-23008-9502
ITEM
43
Discard
(3)
Subtask
C530070-420-001-001
-
Installation.
W
ork
Zones
and
Access
Panels
Zone
Access/W
ork
location
260
Rear
Fuselage
FR43
-
FR45
810
V
entral
door
FR39
-
FR46
Manpower
Resources
Manhours
9.00
Minimum
number
of
person
1
Subtask
elapsed
time
9.00
Skills
Mechanical
Material
necessary
to
do
the
job
Kit
SB235530070K01
ITEM
NEW
P
AR
T
N°
QTY
(UM)
KEYWORD
ITEM
32
95-A1472-0001
1.00
SUPPOR
T
ITEM
34
95-A1473-0101
1.00
FORMER
ITEM
36
95-A1473-0102
1.00
FORMER
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
17
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 18

SER
VICE
BULLETIN
ITEM
38
95-A1473-0301
1.00
FORMER
ITEM
40
95-A1473-0302
1.00
FORMER
ITEM
42
95-A1473-0201
1.00
FORMER
ITEM
44
95-A1473-0202
1.00
FORMER
ITEM
46
95-23138-0101
1.00
FITTING
ITEM
48
95-23138-0102
1.00
FITTING
ITEM
54
95-23137-0101
1.00
FITTING
ITEM
56
95-23137-0102
1.00
FITTING
ITEM
60
95-A1500-0101
1.00
RADIUS
GUARDS
ITEM
61
95-A1500-0102
1.00
RADIUS
GUARDS
ITEM
62
95-A1501-0101
1.00
RADIUS
GUARDS
ITEM
63
95-A1501-0102
1.00
RADIUS
GUARDS
ITEM
64
95-A1502-0101
1.00
RADIUS
GUARDS
ITEM
65
95-A1502-0102
1.00
RADIUS
GUARDS
ITEM
66
95-A1503-0101
1.00
RADIUS
GUARDS
ITEM
67
95-A1503-0102
1.00
RADIUS
GUARDS
ITEM
68
95-A1504-0101
4.00
RADIUS
GUARDS
ITEM
69
95-A1505-0101
4.00
RADIUS
GUARDS
ITEM
301
EN61
15K3-6
4.00
HI-LITE
RIVET
ITEM
302
EN61
15K3-4
1.00
HI-LITE
RIVET
ITEM
303
EN61
15K3-5
9.00
HI-LITE
RIVET
ITEM
304
EN61
15K3-7
22.00
HI-LITE
RIVET
ITEM
305
MS20470E5-6
86.00
RIVET
ITEM
306
MS20470E5-7
76.00
RIVET
ITEM
307
EN61
15K2-3
4.00
HI-LITE
RIVET
ITEM
308
ASNA2536-2
4.00
HI-LITE
NUT
ITEM
309
EN61
15K3-3
4.00
HI-LITE
RIVET
ITEM
31
1
ASNA2536-3
56.00
HI-LITE
NUT
ITEM
312
EN61
15K3-8
12.00
HI-LITE
RIVET
ITEM
313
EN61
15K3-9
4.00
HI-LITE
RIVET
Consumable
CMLS01
ITEM
DESCRIPTION
REFERENCE
CML
QTY
PER
AIRCRAFT
SEALANT
MA
T
.
No.
Z-16.171
A/R
References
Aircraft
Maintenance
Manual
AMM
52-32-23
Structural
Repair
Manual
SRM
51-41-10
Figure
2
Sheet
01
-
Installation.
Sheet
02
-
Installation.
Sheet
03
-
Installation.
Sheet
04
-
Installation.
Sheet
05
-
Installation.
Sheet
06
-
Installation.
NOTE:
Obey
the
minimum
distance
between
the
drill
holes
and
between
the
drill
holes
and
the
edges.
Refer
to
Structural
Repair
Manual
SRM
51-41-10
.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
18
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 19

SER
VICE
BULLETIN
NOTE:
W
et
install
the
rivets
with:
SEALANT
MA
T
.
No.
Z-16.171
A/R
NOTE:
Seal
the
contact
surfaces
with:
SEALANT
MA
T
.
No.
Z-16.171
A/R
NOTE:
If
necessary
,
use
a
shim
with
the
limits
that
follow:
Liquid
0.5
Solid
1
(a)
On
frame
FR43
and
stringers
STGR0A
and
STGR0A
’,
install
the
support
(32),
the
formers
(34)
and
(36)
and
the
fittings
(54)
and
(56).
T
o
do
this:
Refer
to
FIG.
2
Sheet
01
.
Refer
to
FIG.
2
Sheet
02
.
Refer
to
FIG.
2
Sheet
03
.
Refer
to
FIG.
2
Sheet
04
.
1
Put
the
support
(32)
on
the
structure
as
shown
in
the
figure.
2
Use
the
structure
as
a
template
to
do
the
drill
holes
in
the
support
(32).
3
Use
the
support
(32)
as
a
template
to
do
the
drill
holes
in
the
structure.
4
Remove
the
support
(32).
5
Drill
to
the
final
diameter
and
remove
the
burrs.
6
Put
the
formers
(34)
and
(36)
and
the
fittings
(54)
and
(56)
on
the
structure
together
with
the
radius
guards
(60),
(61),
(64),
(65),
(66),
(67)
and
(69),
as
shown
in
the
figure.
7
Use
the
structure
as
a
template
to
do
the
drill
holes
in
the
formers
(34)
and
(36)
and
in
the
fittings
(54)
and
(56).
8
Use
the
formers
(34)
and
(36)
as
a
template
to
do
the
drill
holes
in
the
structure.
9
Use
the
fittings
(54)
and
(56)
as
a
template
to
do
the
drill
holes
in
the
formers
(34)
and
(36).
10
Remove
the
formers,
fittings
and
radius
guards.
1
1
Drill
to
the
final
diameter
and
remove
the
burrs.
12
Attach
the
support
(32),
the
formers
(34)
and
(36)
and
the
fittings
(54)
and
(56)
together
with
the
radius
guards
(60),
(61),
(64),
(65),
(66),
(67)
and
(69).
T
o
do
this,
use
4
rivets
(301),
1
rivet
(302),
9
rivets
(303),
12
rivets
(304),
26
rivets
(305),
38
rivets
(306),
4
rivets
(312),
4
rivets
(313)
and
34
nuts
(31
1).
1
SUPPOR
T
95-A1472-0001
ITEM
32
1
FORMER
95-A1473-0101
ITEM
34
1
FORMER
95-A1473-0102
ITEM
36
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
19
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 20

SER
VICE
BULLETIN
1
FITTING
95-23137-0101
ITEM
54
1
FITTING
95-23137-0102
ITEM
56
1
RADIUS
GUARDS
95-A1500-0101
ITEM
60
1
RADIUS
GUARDS
95-A1500-0102
ITEM
61
1
RADIUS
GUARDS
95-A1502-0101
ITEM
64
1
RADIUS
GUARDS
95-A1502-0102
ITEM
65
1
RADIUS
GUARDS
95-A1503-0101
ITEM
66
1
RADIUS
GUARDS
95-A1503-0102
ITEM
67
4
RADIUS
GUARDS
95-A1505-0101
ITEM
69
4
HI-LITE
RIVET
EN61
15K3-6
ITEM
301
1
HI-LITE
RIVET
EN61
15K3-4
ITEM
302
9
HI-LITE
RIVET
EN61
15K3-5
ITEM
303
12
HI-LITE
RIVET
EN61
15K3-7
ITEM
304
26
RIVET
MS20470E5-6
ITEM
305
38
RIVET
MS20470E5-7
ITEM
306
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
20
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 21

SER
VICE
BULLETIN
34
HI-LITE
NUT
ASNA2536-3
ITEM
31
1
4
HI-LITE
RIVET
EN61
15K3-8
ITEM
312
4
HI-LITE
RIVET
EN61
15K3-9
ITEM
313
(b)
On
frame
FR43
and
stringers
STGR1
and
STGR1’,
install
the
formers
(38)
and
(40).
T
o
do
this:
Refer
to
FIG.
2
Sheet
04
.
NOTE:
This
document
gives
the
procedure
to
do
on
the
left
side.
Do
the
same
procedure
on
the
right
side
with:
1
FORMER
95-A1473-0302
ITEM
40
15
RIVET
MS20470E5-6
ITEM
305
2
HI-LITE
RIVET
EN61
15K2-3
ITEM
307
2
HI-LITE
NUT
ASNA2536-2
ITEM
308
2
HI-LITE
RIVET
EN61
15K3-3
ITEM
309
2
HI-LITE
NUT
ASNA2536-3
ITEM
31
1
1
Put
the
former
(38)
on
the
structure
as
shown
in
the
figure.
2
Use
the
structure
as
a
template
to
do
the
drill
holes
in
the
former
(38).
3
Use
the
former
(38)
as
a
template
to
do
the
drill
holes
in
the
structure.
4
Remove
the
former
(38).
5
Drill
to
the
final
diameter
and
remove
the
burrs.
6
Attach
the
former
(38)
with
15
rivets
(305),
2
rivets
(307),
2
nuts
(308),
2
rivets
(309)
and
2
nuts
(31
1).
1
FORMER
95-A1473-0301
ITEM
38
15
RIVET
MS20470E5-6
ITEM
305
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
21
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 22

SER
VICE
BULLETIN
2
HI-LITE
RIVET
EN61
15K2-3
ITEM
307
2
HI-LITE
NUT
ASNA2536-2
ITEM
308
2
HI-LITE
RIVET
EN61
15K3-3
ITEM
309
2
HI-LITE
NUT
ASNA2536-3
ITEM
31
1
(c)
On
frame
FR44
and
stringers
STGR0A
and
STGR0A
’,
install
the
formers
(42)
and
(44)
and
the
fittings
(46)
and
(48).
T
o
do
this:
Refer
to
FIG.
2
Sheet
04
.
Refer
to
FIG.
2
Sheet
05
.
Refer
to
FIG.
2
Sheet
06
.
NOTE:
This
document
gives
the
procedure
to
do
on
the
left
side.
Do
the
same
procedure
on
the
right
side
with:
1
FORMER
95-A1473-0202
ITEM
44
1
FITTING
95-23138-0102
ITEM
48
1
RADIUS
GUARDS
95-A1501-0102
ITEM
63
2
RADIUS
GUARDS
95-A1504-0101
ITEM
68
5
HI-LITE
RIVET
EN61
15K3-7
ITEM
304
15
RIVET
MS20470E5-6
ITEM
305
19
RIVET
MS20470E5-7
ITEM
306
9
HI-LITE
NUT
ASNA2536-3
ITEM
31
1
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
22
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 23

SER
VICE
BULLETIN
4
HI-LITE
RIVET
EN61
15K3-8
ITEM
312
1
Put
the
former
(42)
on
the
structure
together
with
the
radius
guards
(62)
and
(68),
as
shown
in
the
figure.
2
Use
the
structure
as
a
template
to
do
the
drill
holes
in
the
former
(42)
and
in
the
radius
guards
(62)
and
(68).
3
Use
the
former
(42)
as
a
template
to
do
the
drill
holes
in
the
structure.
4
Remove
the
former
(42).
5
Drill
to
the
final
diameter
and
remove
the
burrs.
6
Put
the
fitting
(46)
on
the
structure
and
on
the
former
(34)
as
shown
in
the
figure.
7
Use
the
structure
as
a
template
to
do
the
drill
holes
in
the
fitting
(46).
8
Use
the
fitting
(46)
as
a
template
to
do
the
drill
holes
in
the
former
(34).
9
Remove
the
fitting
(46).
10
Drill
to
the
final
diameter
and
remove
the
burrs.
1
1
Attach
the
former
(42)
and
the
fitting
(46)
together
with
the
radius
guards
(62)
and
(68).
T
o
do
this,
use
5
rivets
(304),
4
rivets
(312),
15
rivets
(305),
19
rivets
(306)
and
9
nuts
(31
1).
1
FORMER
95-A1473-0201
ITEM
42
1
FITTING
95-23138-0101
ITEM
46
1
RADIUS
GUARDS
95-A1501-0101
ITEM
62
2
RADIUS
GUARDS
95-A1504-0101
ITEM
68
5
HI-LITE
RIVET
EN61
15K3-7
ITEM
304
15
RIVET
MS20470E5-6
ITEM
305
19
RIVET
MS20470E5-7
ITEM
306
9
HI-LITE
NUT
ASNA2536-3
ITEM
31
1
4
HI-LITE
RIVET
EN61
15K3-8
ITEM
312
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
23
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 24

SER
VICE
BULLETIN
(d)
Install
the
kept
V
entral
Door
Actuator
.
Refer
to
Aircraft
Maintenance
Manual
AMM
52-32-23
.
D.
TEST
CONF
001
(1)
Subtask
C530070-700-001-001
-
T
ests.
W
ork
Zones
and
Access
Panels
Zone
Access/W
ork
location
260
Rear
Fuselage
FR43
-
FR45
810
V
entral
door
FR39
-
FR46
Manpower
Resources
Manhours
1.00
Minimum
number
of
person
1
Subtask
elapsed
time
1.00
Skills
Non
specific
References
Aircraft
Maintenance
Manual
AMM
52-32-23
(a)
Remove
the
safety
clips
with
tags
and
close
the
circuit
breakers
that
you
opened.
(b)
Do
the
tests
given
in
the
installation
of
the
V
entral
Door
Actuator
.
Refer
to
Aircraft
Maintenance
Manual
AMM
52-32-23
.
E.
CLOSE
UP
CONF
001
(1)
Subtask
C530070-942-001-001
-
Close-up.
Manpower
Resources
Skills
Non
specific
(a)
Remove
all
the
tools
and
equipment
from
the
work
area.
Make
sure
that
the
work
area
is
clean
and
free
from
tools,
equipment
and
other
items.
(b)
Remove
the
warning
notices.
(c)
Make
sure
that
you
removed
all
the
tools
and
equipment
from
the
area
around
the
aircraft.
(2)
Subtask
C530070-839-001-001
-
Documentation.
Manpower
Resources
Skills
Non
specific
(a)
W
rite
in
the
applicable
aircraft
records
(Aircraft
Modification
Logbook)
that
you
have
done
all
the
work
given
in
this
Service
Bulletin.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
24
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 25

SER
VICE
BULLETIN
This
Page
Intentionally
Left
Blank.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
25
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 26

SER
VICE
BULLETIN
CONF
001,
B
STGR1
STGR0A
STGR0A
B
C
H
A
01
02
03
04
05
− −
−
MIN.
MAX.
341 4.03
4.24
01 02
01 02 03 04 05
’
’
STGR0A STGR0A
’
35
33
31
A
REMOVE AND DISCARD THE RIVET.
NOTE:
BE VERY CAREFUL WHEN YOU REMOVE THE RIVETS.
DO NOT MAKE THE DRILL HOLES LARGER OR OVAL.
COUNTERSINK THE DRILL HOLE ON BOTH SIDES AND FILL WITH THE R IVET (341).
IF IT IS NOT POSSIBLE TO FILL WITH THE RIVET (341), SEAL THE  DRILL HOLE WITH
SEALANT MAT. No. Z−16.177.
RIVET HEAD ON FAR SIDE.
WET INSTALLATION OF THE RIVETS WITH SEALANT MAT. No. Z−16.17
1.
SYMBOL
ITEM
DIAMETER
REMARKS
Figure
1
-
Sheet
01
Removal
and
Configuration
of
the
W
ork
Area.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
26
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 27

SER
VICE
BULLETIN
CONF
001,
STGR1
STGR0A
01
02
− −
−
01 02
D
E
C
F
G
STGR1’
STGR0A’
STGR1
37
33
35
39
D
E
F
STGR1’
STGR0A’
39
37
33
35
37
39
LH
RH
STGR1
STGR1’
LH
RH
G
37
39
LH
RH
STGR1
LH
RH
FR43
LH
RH
STGR0A
STGR0A’
33
35
LH
RH
REMOVE AND DISCARD THE RIVET.
BE VERY CAREFUL WHEN YOU REMOVE THE RIVETS.
DO NOT MAKE THE DRILL HOLES LARGER OR OVAL.
SYMBOL
ITEM
DIAMETER
REMARKS
NOTE:
LH NEAR SIDE
RH SYMMETRICAL
LH NEAR SIDE
RH SYMMETRICAL
LH NEAR SIDE
RH SYMMETRICAL
MIN.
MAX.
Figure
1
-
Sheet
02
Removal
and
Configuration
of
the
W
ork
Area.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
27
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 28

SER
VICE
BULLETIN
CONF
001,
H
K
J
J
STGR1’
STGR0A’
STGR0A
STGR1
LH
RH
LH
RH
K
FR44
LH
RH
LH
RH43
41
43
41
43
41
L
L
L
FR44
322
320
322
321
320
71
72
1
BP
AMM 20−28−00
BP
321
=
=
14
71
72
71
72
09
08
SEE NOTES AND KEYS ON THE SHEET THAT FOLLOWS.
NOTE:
NUMBER OF
ELECTRICAL BONDING
(CONTACT POINTS)
LH NEAR SIDE
RH SYMMETRICAL
AFTERBEFORE
LH NEAR SIDE
RH SYMMETRICAL
Figure
1
-
Sheet
03
Removal
and
Configuration
of
the
W
ork
Area.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
28
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 29

SER
VICE
BULLETIN
CONF
001,
− −
−
01
02
01 02
310 2.49
2.61
01 02
310 2.49
2.61
04
05
03 05 06
06
05
04
03
07
07
MIN.
MAX.
08
09
6.4
6.6
321
322
  
FILL WITH THE RIVET (310). IF IT IS NOT POSSIBLE TO FILL WIT H THE RIVET (310),
SEAL WITH SEALANT MAT. No. Z−16.177.
NOTE:
REMOVE AND DISCARD THE RIVET.
BE VERY CAREFUL WHEN YOU REMOVE THE RIVETS.
DO NOT MAKE THE DRILL HOLES LARGER OR OVAL.
SYMBOL
ITEM
DIAMETER
REMARKS
USE THE NUT (320) AS A TEMPLATE TO DO THE DRILL HOLE IN THE STRUCTURE.
RIVET HEAD ON NEAR SIDE.
COUNTERSINK THE DRILL HOLE ON NEAR SIDE.
WET INSTALLATION OF THE RIVETS WITH SEALANT MAT. No. Z−16.17
1.
SEAL THE DRILL HOLE WITH SEALANT MAT. No. Z−16.177.
APPLY SEALANT MAT. No. Z−16.176 AND VARNISH MAT. No. Z−12.56
0.
Figure
1
-
Sheet
04
Removal
and
Configuration
of
the
W
ork
Area.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
29
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 30

SER
VICE
BULLETIN
CONF
001,
STGR1
STGR0A
STGR0A
B
A
’
’
C
A
STGR0A STGR0A
’
B
= =
06
06
06
06
06
65
69
69
67
66
64
69
60
61
54
34
36
56
32
69
SEE NOTES AND KEYS ON THE SHEET THAT FOLLOWS.
NOTE:
Figure
2
-
Sheet
01
Installation.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
30
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 31

SER
VICE
BULLETIN
CONF
001,
05
05
05
01
02
03
04
05
06
312
311
4.738
4.788
MIN.
MAX.
301
311
4.738
4.788
301
311
4.738
4.788
302
311
4.738
4.788
303
311
4.738
4.788
303
311
4.738
4.788
304
311
4.738
4.788
313
311
4.738
4.788
304
311
4.738
4.788
304
311
4.738
4.788
02 05
04 05
01 05
03 05
04 05
03
04
02
01
05
05
05
05
312
311
4.738
4.788
313
311
4.738
4.788
07
07
07
07
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE SUPPORT (32),
IN THE FORMER (34) LH / (36) RH AND IN THE RADIUS GUARD.
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE SUPPORT (32),
IN THE FITTING (54) LH / (56) RH AND IN THE RADIUS GUARD.
NOTE:
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE SUPPORT (32)
AND IN THE FORMER (34) LH / (36) RH.
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL 
USE THE SUPPORT (32) AS A TEMPLATE TO DO THE DRILL HOLE IN T HE STRUCTURE
AND IN THE FITTING (54) LH / (56) RH.
RIVET HEAD ON NEAR SIDE.
SEAL THE CONTACT SURFACES WITH SEALANT MAT. No. Z−16.171.
DO NEW DRILL HOLES. MAKE SURE THAT YOU OBEY THE DISTANCES TO  THE EDGE AS
SHOWN IN SRM 51−41−10.
SYMBOL
ITEM
DIAMETER
REMARKS
Figure
2
-
Sheet
02
Installation.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
31
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 32

SER
VICE
BULLETIN
CONF
001,
C
D
STGR1’
STGR0A’
STGR0A
STGR1
J
D
E
F
K
H
E
STGR0A’
STGR0A
FR44
LH
RH
LH
RH
LH
RH
LH
RH
09
09
09
36
34
56
54
48
46
38
54
34
36
42
44
40
56
36
34
44
42
09
09
09
SEE NOTES AND KEYS ON THE SHEET THAT FOLLOWS.
NOTE:
LH NEAR SIDE
RH SYMMETRICAL
Figure
2
-
Sheet
03
Installation.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
32
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 33

SER
VICE
BULLETIN
CONF
001,
01
02
03
04
05
06
4.04
4.34
MIN.
MAX.
4.04
4.19
4.04
4.34
4.04
4.19
4.04
4.19
306
4.04
4.19
307
308
4.078
4.128
309
311
4.738
4.788
05
03
04
05
02
01
09
08
07
07
06
08
08
07 08
07 08
06 07 08
07 08
07 08
08
306
305
305
305
305
F
LH
RH
38
40
G
STGR1
STGR1’
LH
RH
FR43
G
38
40
LH
RH
STGR1
STGR1’
LH
RH
09
09
09
09
09
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE
FORMER (34) LH / (36) RH.
USE THE FITTING (54) LH / (56) RH AS A TEMPLATE TO DO THE DR ILL HOLE IN
THE FORMER (34) LH / (36) RH.
USE THE FITTING (46) LH / (48) RH AS A TEMPLATE TO DO THE DR ILL HOLE IN
THE FORMER (34) LH / (36) RH.
USE THE FORMER (38) LH / (40) RH AS A TEMPLATE TO DO THE DRI LL HOLE IN
THE STRUCTURE.
DO NEW DRILL HOLES. MAKE SURE THAT YOU OBEY THE DISTANCES TO  THE EDGE AS
SHOWN IN SRM 51−41−10.
SYMBOL
ITEM
DIAMETER
REMARKS
WET INSTALLATION OF THE RIVETS WITH SEALANT MAT. No. Z−16.17
1.
RIVET HEAD ON NEAR SIDE.
SEAL THE CONTACT SURFACES WITH SEALANT MAT. No. Z−16.171.
USE THE FORMER (34) LH / (36) RH AS A TEMPLATE TO DO THE DRI LL HOLE IN
THE STRUCTURE.
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE
FORMER (38) LH / (40) RH.
LH NEAR SIDE
RH SYMMETRICAL
NOTE:
LH NEAR SIDE
RH SYMMETRICAL
Figure
2
-
Sheet
04
Installation.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
33
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 34

SER
VICE
BULLETIN
CONF
001,
K
’
’
’
’
LH
RH
LH
RH
FR44
FR44
H
J
L
LH
RH
LH
RH
07
07
07
07
44
42
44
42
42
44
42
44
46
48
62
63
LH
RH
68
68
L
SEE NOTES AND KEYS ON THE SHEET THAT FOLLOWS.
LH NEAR SIDE
RH SYMMETRICAL
NOTE:
LH NEAR SIDE
RH SYMMETRICAL
Figure
2
-
Sheet
05
Installation.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
34
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 35

SER
VICE
BULLETIN
CONF
001,
305
4.04
4.34
305
4.04
4.19
304
311
4.738
4.788
312
311
4.738
4.788
03
04
03
04
02
01
05
05
06
06
MIN.
MAX.
SEAL THE CONTACT SURFACES WITH SEALANT MAT. No. Z−16.171.
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE
FORMER (42) LH / (44) RH.
NOTE:
USE THE FORMER (42) LH / (44) RH AS A TEMPLATE TO DO THE DRI LL HOLE
IN THE STRUCTURE.
USE THE STRUCTURE AS A TEMPLATE TO DO THE DRILL HOLE IN THE
FORMER (42) LH / (44) RH, IN THE FITTING (46) LH / (48) RH A ND IN THE RADIUS GUARD.
WET INSTALLATION OF THE RIVETS WITH SEALANT MAT. No. Z−16.17
1.
RIVET HEAD ON FAR SIDE.
RIVET HEAD ON NEAR SIDE.
DO NEW DRILL HOLES. MAKE SURE THAT YOU OBEY THE DISTANCES TO  THE EDGE AS
SHOWN IN SRM 51−41−10.
SYMBOL
ITEM
DIAMETER
REMARKS
01
02
03
04
05
06
07
Figure
2
-
Sheet
06
Installation.
DA
TE:
2022-05-23
SER
VICE
BULLETIN
No.:
SB-235-53-0070C
REVISION
No.:
00
Page:
35
Printed
in
Spain
©
AIRBUS
DEFENCE
AND
SP
ACE
S.A.
SOCIEDAD
UNIPERSONAL
2022.
All
rights
reserved.

### Page 36

SER
VICE
BULLETIN
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Page
Intentionally
Left
Blank.
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TE:
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SER
VICE
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REVISION
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AIRBUS
DEFENCE
AND
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ACE
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SOCIEDAD
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2022.
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rights
reserved.

### Page 37 (OCR)

4. APPENDICES
CONF 002

### Page 38

ANEXO I 
MSN Reparación 
C-143 TEA-3-RA-190125

### Page 39

SER
VICE
BULLETIN
REPOR
TING
SHEET
TITLE:
FUSELAGE.
REAR
FUSELAGE.
REINFORCEMENT
OF
THE
STRUCTURE
BETWEEN
FRAMES
FR43
AND
FR45.
DESIGN
CHANGE
No.:
DC1
1332-E
General
Information:
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### Page 40

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VICE
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### Page 41

SER
VICE
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PERCEPTION
FORM
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