# Airbus Service Bulletin A330-27-3143

Copy: Revision 01 ("FAA-2016-9393_A330-27-3143 Rev01"), 59 pages: PDF https://openairdocs.org/files/sha256/fd/a6/fda6dc9723302b0cf092d4f5c2f9a1c42c811efa01ffe86763554f27f9e84b9e; text https://openairdocs.org/service-documents/airbus/a330-27-3143/file/fda6dc972330.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9393; AD 2017-13-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A330-27-3143
- Latest revision known: A330-27-3143, Revision 01, dated July 10, 2012 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a330-27-3143

## ADs that cite it (2) (OpenAirDocs)

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

- [AD 2017-20-02](https://openairdocs.org/ad/2017-20-02.md), effective Oct 12, 2017: Revision 01
- [AD 2017-13-05](https://openairdocs.org/ad/2017-13-05.md), effective Aug 28, 2017: Revision 01

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a330-27-3143/proposed.md).

## Text (59 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9393; AD 2017-13-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 27
TITLE: FLIGHT CONTROLS - TRIMMABLE HORIZONTAL STABILIZER -
INTRODUCE MODIFIED THSA (P/N 47147-700).
MODIFICATION No.: 54881D46193
This page transmits Revision No.01 of Service Bulletin No.A330-27-3143
ADDITIONAL WORK
**CONF ALL
Additional work is required by this revision for aircraft which have accomplished CONFIG 001 of this
Service Bulletin at initial issue.
REASON
Revision No. 01 issued to modify the Configuration Definition Paragraph and to add TASK
273143-831-802-001.
CHANGES
SUMMARY
MANPOWER
 MANPOWER UPDATED
 R
PLANNING INFORMATION
EFFECTIVITY
 EFFECTIVITY RELATED INFORMATION
UPDATED
R
Configuration definition
CONF 001
 CONFIGURATION DEFINITION UPDATED
CONFIGURATION DESCRIPTION UPDATED
R
CONF 002
 CONFIGURATION DEFINITION UPDATED
CONFIGURATION DESCRIPTION UPDATED
R
MANPOWER
 MANPOWER UPDATED
 R
MATERIAL INFORMATION
MATERIAL - PRICE AND AVAILABILITY
Price and Availability
 PRICE AND AVAILABILITY UPDATED
 R
INDUSTRY SUPPORT INFORMATION
 INDUSTRY SUPPORT INFORMATION UPDATED
 R
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
ACCOMPLISHMENT INSTRUCTIONS
TASK 273143- 831-802-001-Modification -
Additional Work
TASK SOLUTION ADDED
 N
Task associated data - 001
 TASK ASSOCIATED DATA ADDED
 N
Task associated data - 002
 TASK ASSOCIATED DATA ADDED
 N
Subtask 273143-839-002-001
 SUBTASK SOLUTION ADDED
 N
Subtask 273143-910-002-001
 SUBTASK SOLUTION ADDED
 N
Subtask 273143-941-002-001
 SUBTASK SOLUTION ADDED
 N
Subtask 273143-831-004-002
 SUBTASK SOLUTION ADDED
 N
Subtask 273143-831-005-002
 SUBTASK SOLUTION ADDED
 N
Subtask 273143-700-002-002
 SUBTASK SOLUTION ADDED
 N
Subtask 273143-942-003-002
 SUBTASK SOLUTION ADDED
 N
Fig. A-FBCAA
 FIGURE SOLUTION ADDED
 N
Fig. A-FBCAA Sheet 01
 SHEET ADDED
 N
Fig. A-FBCAA Sheet 02
 SHEET ADDED
 N
FILLING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
No previous revision
REVISION SEQUENCE
ORIGINAL: Feb 21/12
REVISION No. : 01 - Jul 10/12
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A330
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 27
TITLE: FLIGHT CONTROLS - TRIMMABLE HORIZONTAL STABILIZER -
INTRODUCE MODIFIED THSA (P/N 47147-700).
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 54881D46193
MINOR
 None
NOTE
: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting the
airworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
The Trimmable Horizontal Stabilizer Actuator (THSA) has a ball-nut, which forms the primary load path
and a threaded nut as the secondary load path. Both run on the screw shaft. In the event of a failure of
the primary load path, loads are transferred to the secondary load path. When the secondary nut is
loaded, the friction increases between the titanium nut and steel screw due to material characteristics.
Investigations of the THSA trans fer tube have indicated that, under ce rtain cyclic load conditions, the
THSA secondary nut does not lock the THSA as expected, but continues to operate with high friction.
This results in damage to the screw and the secondary nut. Operation of the secondary load path is
detected by the Flight Control Primary Computers (FCPC) if the THSA efficiency decreases, to such an
extent that the position error monitoring threshold is exceeded. If this condition remains undetected, a
primary load path failure may result in damage to the screw and secondary nut and, in extreme cases,
in failure of the actuator.
This Service Bulletin is published to advise all operators of A330 aircraft of the issue of GOODRICH
ACTUATION SYSTEMS Service Bulletin No 47147-27-11.
This Service Bulletin requires the installation of two Electrical Detection Devices (EDD) on the lower
attachment secondary load path of the THSA. This EDD is called a "Checkable Shear Pin". The
Checkable Shear Pins are installed on each side of the lower attachment to cover the load sharing
cases.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A330
SERVICE BULLETIN
SUMMARY
Accomplishment of this Service Bulletin in simultaneous combination with Service Bulletin
No.A330-92-3046 or with MOD 52269 embodied by production, will give to the FCPCs a failure
indication of the primary load path of the THSA.
Accomplishment of this Service Bulletin in simultaneous combination with Service Bulletin No.
A330-92-3046 or with MOD 52269 embodied by production, will permit to revoke the mandated 700FH
THSA inspection introduced per AD 2010-0192.
This Service Bulletin cancels the requirements introduced by the Inspection Service Bulletin No.
A330-27-3102.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 MANDATORY (1)
 CANCELS INSPECTION SB
 YES
POTENTIAL AD
 YES
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 YES
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
**CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Equipment BFEA01
 1
 See SB
 THSA
**CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Equipment BFEA01
 1
 See SB
 THSA
Component COMPA01
 1
 See SB
 BOLT
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
BEL BER CPA GIA HDA HFY KAL MAS OHY PAL RSY THA TSC
VLK XAX
CONCURRENT REQUIREMENTS
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the
following Service Bulletins or the equivalent production modifications :
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A330
SERVICE BULLETIN
SUMMARY
Service Bulletin No. A330-27-3093 Mod. No. 49591D44011
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 NO
EQUIPMENT
 YES
HARD
 YES
SOFT
 NO
OBRM
 NO
MANPOWER
**CONF 001
Task 273143-831-801-001: Modification
TOTAL MANHOURS
 4.00
ELAPSED TIME (HOURS)
 4.00
Additional manhours relat ed to Vendor SB; refer to:
Modify the Trimmable Horizontal Stabilizer Actuator
(THSA) FIN 1CS on aircraft.
GOODRICH ACTUATION
SYSTEMS SA Service Bulletin No.
47147-27-11
**CONF 002
Task 273143-831-801-001: Modification
TOTAL MANHOURS
 5.00
ELAPSED TIME (HOURS)
 5.00
Additional manhours relat ed to Vendor SB; refer to:
Modify the Trimmable Horizontal Stabilizer Actuator
(THSA) FIN 1CS on aircraft.
GOODRICH ACTUATION
SYSTEMS SA Service Bulletin No.
47147-27-11
Task 273143-831-802-001: Modification - Additional Work
TOTAL MANHOURS
 5.00
ELAPSED TIME (HOURS)
 5.00
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A330
SERVICE BULLETIN
SUMMARY
APPENDICES
**CONF ALL
None
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A330
SERVICE BULLETIN
SUMMARY
**CONF 001
ACCESS
PANEL
Z310
A
312AR
FR80
FR87
AFTER
CSP
CONNECTOR
A
G_SB_273143_5_SAAA_01_01
B
B
Figure A-FSAAA - Sheet 01
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A330
SERVICE BULLETIN
SUMMARY
**CONF 002
ACCESS
PANEL
Z310
A
312AR
FR80
FR87
AFTER
CSP
CONNECTOR
A
B
B
G_SB_273143_5_SAAB_01_00
Figure A-FSAAB - Sheet 01
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A330
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 27
TITLE: FLIGHT CONTROLS - TRIMMABLE HORIZONTAL STABILIZER -
INTRODUCE MODIFIED THSA (P/N 47147-700).
MODIFICATION No.: 54881D46193
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS 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 prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE
: This modification is applicable by Service Bulletin Only.
NOTE
: This Service Bulletin is only applicable to aircraft equipped with THS Actuator
PN 47147-500.
(1) Models
330-301 330-321 330-322 330-341 330-342
(2) Effectivity by MSN
0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0067 0069-0073 0077
0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0113 0116
0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172
0177 0183-0184 0188-0189 0191 0198 0200 0203 0206 0209 0219 0224 0231
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A330
SERVICE BULLETIN
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. 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.
OPERATOR
 MSN
BEL
 0030 0037 0045 0082 0095
BER
 0120 0127
CPA
 0012 0017 0071 0102 0113 0118 0121 0155
GIA
 0138 0140 0144 0148 0153 0165
HDA
 0083 0099 0106 0109
HFY
 0096
KAL
 0162 0172 0206 0219
MAS
 0067 0069 0073 0077 0100 0107 0110 0116 0119
OHY
 0072 0087 0098 0143
PAL
 0183 0184 0188 0189 0191 0198 0200 0203
RSY
 0171
THA
 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231
TSC
 0111 0132 0177
VLK
 0055 0070 0086
XAX
 0054
(4) Configuration by MSN
MSN
 CONFIGURATION
0012 0017 0030 0037 0050 0055 0060 0062 0064 0065 0066
0070 0071 0072 0082 0083 0086 0087 0095 0096 0098 0099
0106 0111 0112 0118 0122 0138 0140 0144 0148 0153 0155
0165 0183 0184 0188 0189 0191 0198 0200 0203 0209 0224
0231
001 002
0045 0054 0067 0069 0073 0077 0100 0102 0107 0109 0110
0113 0116 0119 0120 0121
 0127 0132
 0143 0162
 0171 0172
0177 0206
 0219
002
(5) Configuration definition
**CONF 001
Config. 001 is valid for aircraft on which Service Bulletin No A330-92-3046 is not
accomplished or Modification No 52269 D44449 is not embodied in production and
details the work necessary to embody the modification with the THSA installed on the
aircraft.
**CONF 002
Config. 002 is valid for aircraft on which Service Bulletin No A330-92-3046 is
accomplished or Modification No 52269 D44449 is embodied in production and details
the work necessary to embody the modification with the THSA installed on the aircraft.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A330
SERVICE BULLETIN
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Equipment BFEA01
 1
**CONF 002
MATERIAL
 QTY PER A/C
 SEE NOTES
Equipment BFEA01
 1
Component COMPA01
 1
**CONF ALL
B. CONCURRENT REQUIREMENTS
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of
the following Service Bulletins or the equivalent production modifications :
Service Bulletin No. A330-27-3093 Mod. No. 49591D44011
C. REASON
(1) History
The Trimmable Horizontal Stabilizer Actuator (THSA) has a ball-nut, which forms the
primary load path and a threaded nut as the secondary load path. Both run on the screw
shaft. In the event of a failure of the primary load path, loads are transferred to the
secondary load path. When the secondary nut is loaded, the friction increases between
the titanium nut and steel screw due to material characteristics. Investigations of the
THSA transfer tube have indicated that, under certain cyclic load conditions, the THSA
secondary nut does not lock the THSA as expected, but continues to operate with high
friction. This results in damage to the screw and the secondary nut. Operation of the
secondary load path is detected by the Flight Control Primary Computers (FCPC) if the
THSA efficiency decreases, to such an extent that the position error monitoring threshold
is exceeded. If this condition remains undetected, a primary load path failure may result
in damage to the screw and secondary nut and, in extreme cases, in failure of the
actuator.
(2) Objective/Action
This Service Bulletin is published to advise all operators of A330 aircraft of the issue of
GOODRICH ACTUATION SYSTEMS Ser vice Bulletin No 47147-27-11.
This Service Bulletin requires the installation of two Electrical Detection Devices (EDD)
on the lower attachment secondary load path of the THSA. This EDD is called a
"Checkable Shear Pin". The Checkable Shear Pins are installed on each side of the
lower attachment to cover the load sharing cases.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A330
SERVICE BULLETIN
(3) Advantages
Accomplishment of this Service Bulletin in simultaneous combination with Service
Bulletin No.A330-92-3046 or with MOD 52269 embodied by production, will give to the
FCPCs a failure indication of the primary load path of the THSA.
(4) Operational/Maintenance Consequences
Accomplishment of this Service Bulletin in simultaneous combination with Service
Bulletin No. A330-92-3046 or with MOD 52269 embodied by production, will permit to
revoke the mandated 700FH THSA inspection introduced per AD 2010-0192.
This Service Bulletin cancels the requirements introduced by the Inspection Service
Bulletin No. A330-27-3102.
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
**CONF 001
Task 273143-831-801-001: Modification
(1) Modify the Trimmable Horizontal Stabilizer Actuator (THSA) FIN 1CS on aircraft.
**CONF 002
Task 273143-831-801-001: Modification
(1) Modify the Trimmable Horizontal Stabilizer Actuator (THSA) FIN 1CS on aircraft.
(2) Remove the Closing Plug from the Electrical Harness 4515VB.
(3) Connect the Electrical Harness 4515VB to the THSA.
Task 273143-831-802-001: Modification - Additional Work
(1) Remove the Closing Plug from the Electrical Harness 4515VB.
(2) Connect the Electrical Harness 4515VB to the THSA.
**CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A330
SERVICE BULLETIN
(2) Accomplishment Timescale
This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued
to confirm this classification. The accomplishment timescale, which has not yet been
defined, will be given in the AD.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No. EASA.21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
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
Task 273143-831-801-001: Modification
Get Access
 2.00
On Aircraft
Tests
 0.50
Close-Up
 1.50
TOTAL MANHOURS
 4.00
ELAPSED TIME (HOURS)
 4.00
Additional manhours relat ed to Vendor SB; refer to:
Modify the Trimmable Horizontal Stabilizer Actuator
(THSA) FIN 1CS on aircraft.
GOODRICH ACTUATION
SYSTEMS SA Service Bulletin No.
47147-27-11
**CONF 002
Task 273143-831-801-001: Modification
Get Access
 2.00
On Aircraft
Remove the Closing Plug from the Electrical Harness
4515VB.
0.50
Connect the Electrical Harness 4515VB to the THSA.
 0.50
Tests
 0.50
Close-Up
 1.50
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A330
SERVICE BULLETIN
Task 273143-831-801-001: Modification
TOTAL MANHOURS
 5.00
ELAPSED TIME (HOURS)
 5.00
Additional manhours relat ed to Vendor SB; refer to:
Modify the Trimmable Horizontal Stabilizer Actuator
(THSA) FIN 1CS on aircraft.
GOODRICH ACTUATION
SYSTEMS SA Service Bulletin No.
47147-27-11
Task 273143-831-802-001: Modification - Additional Work
Get Access
 2.00
On Aircraft
Remove the Closing Plug from the Electrical Harness
4515VB.
0.50
Connect the Electrical Harness 4515VB to the THSA.
 0.50
Tests
 0.50
Close-Up
 1.50
TOTAL MANHOURS
 5.00
ELAPSED TIME (HOURS)
 5.00
**CONF ALL
H. WEIGHT AND BALANCE
Manufacturers Empty Weight +3.930 KG (+8.6640 LB)
Effect on Balance +247,523 KGM (+1790.303 LB.FT )
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 06-41-53 12-34-24 27-40-00
27-44-00 27-44-51 29-00-00
29-14-00
ATA Common Support Data Dictionary (CSDD),
Chapter 2
Elec. Std. Practices Manual (ESPM)
 20-33-00 20-55-00
Service Bulletin (SB)
 A330-27-3093
A330-27-3102
A330-92-3046
Vendor Service Bulletin (VSB)
 GOODRICH ACTUATION
SYSTEMS SA Service Bulletin No.
47147-27-11
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 15

@A330
SERVICE BULLETIN
**CONF 002
Aircraft Maintenance Manual (AMM)
 06-41-53 12-34-24 24-41-00
27-40-00 27-44-00 27-44-51
27-96-00 29-00-00 29-14-00
31-60-00
ATA Common Support Data Dictionary (CSDD),
Chapter 2
Elec. Std. Practices Manual (ESPM)
 20-33-00 20-55-00
Service Bulletin (SB)
 A330-27-3093
A330-27-3102
A330-92-3046
Standards Manual (SM)
Vendor Service Bulletin (VSB)
 GOODRICH ACTUATION
SYSTEMS SA Service Bulletin No.
47147-27-11
**CONF ALL
K. PUBLICATION AFFECTED
Aircraft Maintenance Manual (AMM)
 27-44-51 27-44-59
Aircraft Wiring List (AWL)
Illustrated Parts Catalog (IPC)
 27-44-04 27-44-51
Trouble Shooting Manual (TSM)
 27-40-00 27-90-00
L. INTERCHANGEABILITY/MIXABILITY
**CONF 001
DESCRIPTION
 OLD PART N˚
 NEW PART N˚
 INT
 MIXABILITY
 SEE
NOTES
THS-Actuator
 47147-500
 47147-700
 01
 Not
Applicable
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
**CONF 002
DESCRIPTION
 OLD PART N˚
 NEW PART N˚
 INT
 MIXABILITY
 SEE
NOTES
THS-Actuator
 47147-500
 47147-700
 01
 Not
Applicable
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
**CONF ALL
M. SPARES
THS-Actuator 47147-500
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 7
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 16

@A330
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 8
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 17

@A330
SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
Airbus Material, Logistics and Suppliers do not stock standard hardware as competitive
multiple suppliers ensure access to minimum prices.
Airbus recommends Customers with aircraft shown in the effectivity of this Service
Bulletin to send a purchase order to B/E Aerospace. The address is:
Equipment BFEA01
 Modification of removed equipment should be
negotiated directly with Goodrich Actuation
Systems as per instructions given in Service
Bulletin No. 47147-27-11.
Component COMPA01
 B/E AEROSPACE INC
CONSUMABLES MANAGEMENT
10000 NW 15TH Terrace Miami
FL 33172
USA
Tel EMEA : +49 (0) 40 822 285 31500
Tel US : +1 305 925 2600
Tel ASIA : +1 310 900 1300
Fax EMEA : +49 (0) 40 822 285 31010
Fax US : +1 305 507 7191
Fax ASIA : +1 310 819 1200
SITA : MIAMMCR
E-Mail : AOGdesk_CMG@beaerospace.com
web address : www.beconsumables.com
(2) Price and Availability
No Airbus kit will be provided.
Refer to the Vendor Service Bulletin No. 47147-27-11 for the equipment modification
sales terms.
Operator supplied standard hardware parts required to accomplish this Service Bulletin
are to be supplied from the Operator’s stock.
B. INDUSTRY SUPPORT INFORMATION
Refer to the Vendor Service Bulletin No. 47147-27-11 for the industry support terms of the
Vendor Service Bulletin parts and labor.
For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 9
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 18

@A330
SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
France
T e l:( 3 3 )56 71 90 62 2
E-mail : monitored.retrofit@airbus.com
F a x:( 3 3 )56 19 32 74 5
C. LIST OF COMPONENTS
No Kit
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
None
(2) Components
Component COMPA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
11
 NAS6703U4
 2
 BOLT
NOTE
: If you find part numbers of hardware components in the related kit(s)
which you cannot identify in the LIST OF COMPONENTS of this Service
Bulletin, refer to Standards Manual (SM). The SM will give you the
correct part number to part number relationship.
(3) Equipment
Equipment BFEA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 47147-700
 1
 THSA
 (1)
 47147-500
 01
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
None
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 10
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 19

@A330
SERVICE BULLETIN
(2) Tools
NOTE
: To accomplish this Service Bulletin it is necessary to use the tools listed
in the AMM task (Refer to AMM Task 27-44-51-860-050)
(3) Special Tools
None
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 11
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 20

@A330
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 12
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 21

@A330
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 273143-831-801-001 - Modification
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE
IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL
OR INJURE PERSONS.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
LUBRIFICATION OF POST MOD THSA IS TO BE PERFORMED WITH AIMS
09-06-002 (CML 04-037).
Task Associated Data
**CONF 001
Zone
120 210 310
Modified FIN
1CS
Access
Door
 312AR 811 831 831 / 841 841
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 13
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 22

@A330
SERVICE BULLETIN
Manpower
TOTAL MANHOURS
 4.00
ELAPSED TIME (HOURS)
 4.00
Additional manhours related to Vendor SB; refer to:
GOODRICH ACTUATION SYSTEMS SA S ervice Bulletin No. 47147-27-11
**CONF 002
Zone
120 210 310
Modified FIN
1CS
Access
Door
 312AR 811 831 831 / 841 841
Manpower
TOTAL MANHOURS
 5.00
ELAPSED TIME (HOURS)
 5.00
Additional manhours related to Vendor SB; refer to:
GOODRICH ACTUATION SYSTEMS SA S ervice Bulletin No. 47147-27-11
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 273143-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
(2) Subtask 273143-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-53, Page Block 001
Task 29-00-00-910-804
Elec. Std. Practices Manual (ESPM)
 20-33-00
(a) Clean the work area as necessary with Solvent General Purpose (Mat. No. 11-026)
and a Lint-Free Cotton Cloth (Mat. No. 19-003).
(b) Obey the hydraulic safety precautions (Refer to AMM Task 29-00-00-910-804).
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 14
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 23

@A330
SERVICE BULLETIN
(c) For identification of access panels (Refer to AMM 06-41-53, Page Block 001).
(d) Put blanking caps on disconnected hydraulic lines, open ports and electrical
connectors.
(e) For information on installation of Electrical Harness (Refer to ESPM 20-33-00).
**CONF 002
(1) Subtask 273143-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
(2) Subtask 273143-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-53, Page Block 001
Task 29-00-00-910-804
Elec. Std. Practices Manual (ESPM)
 20-33-00
(a) Clean the work area as necessary with Solvent General Purpose (Mat. No. 11-026)
and a Lint-Free Cotton Cloth (Mat. No. 19-003).
(b) Obey the hydraulic safety precautions (Refer to AMM Task 29-00-00-910-804).
(c) For identification of access panels (Refer to AMM 06-41-53, Page Block 001).
(d) Put blanking caps on disconnected hydraulic lines, open ports and electrical
connectors.
(e) For information on installation of Electrical Harness (Refer to ESPM 20-33-00).
**CONF ALL
B. PREPARATION
**CONF 001
(1) Subtask 273143-941-001-001 - Job Set-up
Work Zones and Access Panels
Zone
 Access/Work location
210
 Access
 Door 831, Door 841
310
 Access
 Door 312AR
120
 Access
 Door 811
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 15
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 24

@A330
SERVICE BULLETIN
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 27-40-00-866-801
Task 27-44-51-860-050
Task 29-00-00-864-804
Task 29-14-00-614-802
Task 29-14-00-614-803
(a) Make sure the aircraft is electrically grounded (Refer to AMM Task
12-34-24-860-802).
(b) Move the THS in zero degree position (Refer to AMM Task 27-40-00-866-801).
(c) Install the PITCH-TRIM CONTROL LOCKING (98F27401000000) on the pitch trim
control wheel (Refer to AMM Task 27-44-51-860-050).
(d) Depressurize the Blue and Yellow hydraulic systems(Refer to AMM Task
29-00-00-864-804).
(e) Depressurize the reservoir of the Blue and Yellow hydraulic systems (Refer to AMM
Task 29-14-00-614-802 and AMM Task 29-14-00-614-803).
(f) Put the warning notices in the cockpit, on the panel 215VU and on the panel
990VU, to tell persons:
- not to start the APU.
- not to refuel the aircraft.
- not to pressurize the Blue and Yellow hydraulic systems.
- not to pressurize the reservoirs of the Blue and Yellow hydraulic systems.
- not to operate the THSA actuator.
(g) Put the access platform in position below the access door 811 to get access to the
avionics compartment.
(h) Open, safety and tag these circuit breakers:
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1)
722VU
 FCDC 2
 6CE2
 42 T
 (1)
722VU
 FCSC 2
 10CE2
 37 T
 (1)
722VU
 FCSC 2
 10CE2
 39 T
 (1)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 16
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 25

@A330
SERVICE BULLETIN
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1)
742VU
 FCDC 1
 6CE1
 64 E
 (1)
742VU
 FCDC 1
 6CE1
 65 D
 (1)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
(i) Put an access platform below the access door 312AR.
(j) Open the access door 312AR and set the light switch to the ON position.
(k) Install the MECHANICAL INPUT-RIGGING PIN (OU191067) on the mechanical
input of THS actuator and the ball-nut assembly (Refer to AMM Task
27-44-51-860-050).
(l) Put the TOOL-ZERO LOCATION THSA (OU191066) in position between the THS
actuator and the ball-nut assembly (Refer to AMM Task 27-44-51-860-050).
(m) Safety the upper end of the TOOL-ZERO LOCATION THSA (OU191066) to the
upper claw stop with a tie wrap.
(n) Put the FIXTURE-STRUT, HORIZONTAL STABILIZER PN 98A27407514004
(applicable pre mod 44205 D40465) or PN 98A27407514005 (applicable post mod
44205 D40465) in position and make sure that the THS is in zero degree position
(Refer to AMM Task 27-44-51-860-050).
**CONF 002
(1) Subtask 273143-941-001-001 - Job Set-up
Work Zones and Access Panels
Zone
 Access/Work location
210
 Access
 Door 831, Door 841
310
 Access
 Door 312AR
120
 Access
 Door 811
Manpower Resources
Skills
 NON SPECIFIC
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 17
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 26

@A330
SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 27-40-00-866-801
Task 27-44-51-860-050
Task 29-00-00-864-804
Task 29-14-00-614-802
Task 29-14-00-614-803
(a) Make sure the aircraft is electrically grounded (Refer to AMM Task
12-34-24-860-802).
(b) Move the THS in zero degree position (Refer to AMM Task 27-40-00-866-801).
(c) Install the PITCH-TRIM CONTROL LOCKING (98F27401000000) on the pitch trim
control wheel (Refer to AMM Task 27-44-51-860-050).
(d) Depressurize the Blue and Yellow hydraulic systems(Refer to AMM Task
29-00-00-864-804).
(e) Depressurize the reservoir of the Blue and Yellow hydraulic systems (Refer to AMM
Task 29-14-00-614-802 and AMM Task 29-14-00-614-803).
(f) Put the warning notices in the cockpit, on the panel 215VU and on the panel
990VU, to tell persons:
- not to start the APU.
- not to refuel the aircraft.
- not to pressurize the Blue and Yellow hydraulic systems.
- not to pressurize the reservoirs of the Blue and Yellow hydraulic systems.
- not to operate the THSA actuator.
(g) Put the access platform in position below the access door 811 to get access to the
avionics compartment.
(h) Open, safety and tag these circuit breakers:
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1)
722VU
 FCDC 2
 6CE2
 42 T
 (1)
722VU
 FCSC 2
 10CE2
 37 T
 (1)
722VU
 FCSC 2
 10CE2
 39 T
 (1)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 18
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 27

@A330
SERVICE BULLETIN
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1)
742VU
 FCDC 1
 6CE1
 64 E
 (1)
742VU
 FCDC 1
 6CE1
 65 D
 (1)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
(i) Put an access platform below the access door 312AR.
(j) Open the access door 312AR and set the light switch to the ON position.
(k) Install the MECHANICAL INPUT-RIGGING PIN (OU191067) on the mechanical
input of THS actuator and the ball-nut assembly (Refer to AMM Task
27-44-51-860-050).
(l) Put the TOOL-ZERO LOCATION THSA (OU191066) in position between the THS
actuator and the ball-nut assembly (Refer to AMM Task 27-44-51-860-050).
(m) Safety the upper end of the TOOL-ZERO LOCATION THSA (OU191066) to the
upper claw stop with a tie wrap.
(n) Put the FIXTURE-STRUT, HORIZONTAL STABILIZER PN 98A27407514004
(applicable pre mod 44205 D40465) or PN 98A27407514005 (applicable post mod
44205 D40465) in position and make sure that the THS is in zero degree position
(Refer to AMM Task 27-44-51-860-050).
**CONF ALL
C. PROCEDURE
**CONF 001
(1) Subtask 273143-831-001-003 - Modify the Trimmable Horizontal Stabilizer Actuator
(THSA) FIN 1CS on aircraft.
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 19
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 28

@A330
SERVICE BULLETIN
Material necessary to do the job
Equipment BFEA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 47147-700
 1
 THSA
References
Vendor Service Bulletin (VSB)
 GOODRICH ACTUATION SYSTEMS SA
47147-27-11
Fig. A-FBAAA
Modification of the Trimmable Horizontal
Stabilizer Actuator
Sheet 01
CAUTION
: DURING INSTALLATION OF THE ARMS, MAKE SURE NO
EXCESSIVE EFFORT IS APPLIED ON THE THSA BALL NUT
OTHERWISE CSP PINS MAY SHEAR.
(a) Disconnect the mechanical input shaft from the THS actuator.
(b) Disconnect the electrical connectors and the THS actuator arms.
(c) Remove the THS actuator arms.
(d) Accomplish GOODRICH ACTUATION SYSTEMS SA Service Bulletin No.
47147-27-11.
(e) Install the THS actuator arms.
(f) Connect the electrical connectors.
(g) Connect the mechanical input shaft to the actuator.
(h) After modification:
FIN 1CS
1 THS-Actuator 47147-500 Item (1)
becomes
FIN 1CS
1 THS-Actuator 47147-700 Item 1
**CONF 002
(1) Subtask 273143-831-001-002 - Modify the Trimmable Horizontal Stabilizer Actuator
(THSA) FIN 1CS on aircraft.
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 20
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 29

@A330
SERVICE BULLETIN
Material necessary to do the job
Equipment BFEA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 47147-700
 1
 THSA
References
Vendor Service Bulletin (VSB)
 GOODRICH ACTUATION SYSTEMS SA
47147-27-11
Fig. A-FBAAB
Modification of the Trimmable Horizontal
Stabilizer Actuator
Sheet 01
CAUTION
: DURING INSTALLATION OF THE ARMS, MAKE SURE NO
EXCESSIVE EFFORT IS APPLIED ON THE THSA BALL NUT
OTHERWISE CSP PINS MAY SHEAR.
(a) Disconnect the mechanical input shaft from the THS actuator.
(b) Disconnect the electrical connectors and the THS actuator arms.
(c) Remove the THS actuator arms.
(d) Accomplish GOODRICH ACTUATION SYSTEMS SA Service Bulletin No.
47147-27-11.
(e) Install the THS actuator arms.
(f) Connect the electrical connectors.
(g) Connect the mechanical input shaft to the actuator.
(h) After modification:
FIN 1CS
1 THS-Actuator 47147-500 Item (1)
becomes
FIN 1CS
1 THS-Actuator 47147-700 Item 1
(2) Subtask 273143-831-002-001 - Remove the Closing Plug from the Electrical
Harness 4515VB.
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 21
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 30

@A330
SERVICE BULLETIN
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
References
Fig. A-FBBAA
Removal of the Closing Plug from the
Electrical Harness / Connection of the
Electrical Harness to the THSA
Sheet 01
Sheet 02
(a) Disassemble the electrical harness 4515VB from the supports of the THS front spar
(refer to Fig. A-FBBAA Sheet 01
 ).
2 Screw Item (2) Discard
2 Washer Item (3) Retain
4 Clamp Item (4) Discard
2 Spacer Item (5) Discard
1 Clamp Item (6) Discard
1 Clamp Item (7) Discard
(b) Remove the cable ties, item (9), and the support, item (8), to release the electrical
harness 4515VB.
2 Cable tie Item (9)
1 Support Item (8)
(c) Remove the closing plug, item (10), from the head of the electrical harness
4515VB.
1 Closing Plug Item (10)
(3) Subtask 273143-831-003- 001 - Connect the Electrical Harness 4515VB to the THSA.
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 22
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 31

@A330
SERVICE BULLETIN
Material necessary to do the job
Component COMPA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 NAS6703U4
 2
 BOLT
References
Fig. A-FBBAA
Removal of the Closing Plug from the
Electrical Harness / Connection of the
Electrical Harness to the THSA
Sheet 01
Sheet 02
(a) Install the electrical harness 4515VB.
1
 Attach the electrical harness 4515VB to the supports of the THS front spar
(Refer to Fig. A-FBBAA Sheet 02
 , detail E).
2 Bolt NAS6703U4 Item 11
2 Washer Item (3) Retained at
removal
2
 Attach the electrical harness 4515VB to the bracket of the THSA arm (Refer to
Fig. A-FBBAA Sheet 02
 , detail F).
- Remove and retain:
1 Bolt Item (15) Retain
1 Washer Item (14) Retain
1 Clamp Item (13) Retain
1 Spacer Item (12) Retain
- Install the harness 4515VB:
1 Bolt Item (15) Retained at
removal
1 Washer Item (14) Retained at
removal
1 Clamp Item (13) Retained at
removal
1 Spacer Item (12) Retained at
removal
(b) Remove the closing cap from the THSA CSP connector and connect the electrical
harness 4515VB.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 23
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 32

@A330
SERVICE BULLETIN
**CONF ALL
D. TEST
**CONF 001
(1) Subtask 273143-700-001-001 - Testing
Work Zones and Access Panels
Zone
 Access/Work location
120
 Access
 Door 811
210
 Access
 Door 831 / 841
310
 Access
 Door 312AR
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 27-44-00-710-805
(a) Job Set-Up:
1
 Remove the safety clips and tags and close this (these) following circuit
breakers(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1)
722VU
 FCDC 2
 6CE2
 42 T
 (1)
722VU
 FCSC 2
 10CE2
 37 T
 (1)
722VU
 FCSC 2
 10CE2
 39 T
 (1)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1)
742VU
 FCDC 1
 6CE1
 64 E
 (1)
742VU
 FCDC 1
 6CE1
 65 D
 (1)
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 24
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 33

@A330
SERVICE BULLETIN
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
(b) Procedure:
1
 Do Operational Test of the Trimmable Horizontal Stabilizer ( THS ) Actuator
(Refer to AMM Task 27-44-00-710-805).
**CONF 002
(1) Subtask 273143-700-001-002 - Testing
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
120
 Access
 Door 811
210
 Access
 Door 831 / 841
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 24-41-00-861-801
Task 24-41-00-862-801
Task 27-44-00-710-805
Task 27-44-51-710-801
Task 27-96-00-740-801
Task 29-00-00-863-801
Task 29-00-00-863-802
Task 29-00-00-863-803
Task 29-00-00-864-801
Task 29-00-00-864-802
Task 29-00-00-864-803
Task 31-60-00-860-801
Task 31-60-00-860-802
(a) Job Set-Up:
1
 Remove the safety clips and tags and close this (these) following circuit
breakers(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1)
722VU
 FCDC 2
 6CE2
 42 T
 (1)
722VU
 FCSC 2
 10CE2
 37 T
 (1)
722VU
 FCSC 2
 10CE2
 39 T
 (1)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 25
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 34

@A330
SERVICE BULLETIN
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1)
742VU
 FCDC 1
 6CE1
 64 E
 (1)
742VU
 FCDC 1
 6CE1
 65 D
 (1)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
(b) Procedure:
- Do the Operational Check of THSA Checkable Shear-Pin, (Refer to AMM Task
27-44-51-710-801).
NOTE
: If the SB reference is not specified in the latest operator’s AMM
issue, do these steps:
1
WARNING
: PUT THE SAFETY DEVICES AND THE WARNING NOTICES
IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE
MOVEMENT OF COMPONENTS CAN KILL OR INJURE
PERSONS.
Job Set-Up:
a
WARNING
: MAKE SURE THAT THE PRIM 1 PUSHBUTTON
SWITCH IS PUSHED (OFF AND FAULT LEGENDS
OFF) BEFORE YOU PRESSURIZE THE HYDRAULIC
SYSTEM. IF THE PRIM 1 PUSHBUTTON SWITCH IS
RELEASED (OFF LEGEND ON) THE RUDDER CAN
MOVE AND CAUSE INJURY AND/OR DAMAGE.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 26
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 35

@A330
SERVICE BULLETIN
WARNING
: MAKE SURE THAT THE PRIM 1 PUSHBUTTON
SWITCH IS PUSHED (OFF AND FAULT LEGENDS
OFF) BEFORE YOU PRESSURIZE THE HYDRAULIC
SYSTEM. IF THE PRIM 1 PUSHBUTTON SWITCH IS
RELEASED (OFF LEGEND ON) THE RUDDER CAN
MOVE AND CAUSE INJURY AND/OR DAMAGE.
Aircraft Maintenance configuration.
<1> Energize the aircraft electrical circuits (Refer to AMM Task
24-41-00-861-801).
<2> Do the EIS start procedure (EWD DU, SD DU only) (Refer to AMM
Task 31-60-00-860-801).
<3> Pressurize the aircraft hydraulic systems (Refer to AMM Task
29-00-00-863-801, AMM Task 29-00-00-863-802 and AMM Task
29-00-00-863-803).
<4> Put the WARNING NOTICE(S) in position to tell persons that the
trimmable horizontal stabilizer (THS) is in operation.
<5> On the FLT CTL section of the overhead panel 241VU, make sure
that the PRIM 1 and SEC 1 P/BSWs are released (OFF legends are
on).
<6> On the FLT CTL section of the overhead panel 212VU, make sure
that the PRIM 2, PRIM 3 and SEC 2 P/BSWs are released (OFF
legends are on).
b
 On the ECAM control panel, push the C/B key (on the SD the C/B page
comes into view). Make sure that the SD does not show this(these)
circuit breaker(s) :
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1)
722VU
 FCDC 2
 6CE2
 42 T
 (1)
722VU
 FCSC 2
 10CE2
 37 T
 (1)
722VU
 FCSC 2
 10CE2
 39 T
 (1)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1)
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 27
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 36

@A330
SERVICE BULLETIN
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1)
742VU
 FCDC 1
 6CE1
 64 E
 (1)
742VU
 FCDC 1
 6CE1
 65 D
 (1)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
2
 Procedure
a
 Operational Test of the Checkable Shear-Pin.
NOTE
: Two persons are necessary to do this procedure:
- One person at the THSA to push the checkable
shear-pin check button.
- One person in the cockpit to read the messages,
push the P/BSW’s and turn the pitch-trim control
wheel.
NOTE
: You must do this procedure for one checkable shear-pin,
then you must do the test again for the other checkable
shear-pin.
ACTION
 RESULT
Operational Test of the Checkable Shear-Pin with the PRIM 2
1. On the ECAM control panel:
- Push the F/CTL key.
On the SD:
- The F/CTL page comes into view.
2. On the FLT CTL panels 212VU:
- Push the PRIM 2 P/BSW.
NOTE
: When you push the PRIM 2
P/BSW, a trim setting will start.
You must wait until the trim setting
has completed before you continue
with step 3.
On the FLT CTL panels 212VU:
- The OFF/R legend of the PRIM 2 P/BSW goes
off.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator goes white.
On the center pedestal:
- The pitch-trim control wheel goes to 4 deg. UP.
- On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows 4 deg. UP
plus or minus 0.4 deg.
3. On the center pedestal:
- Turn the pitch-trim control wheel to the 13 deg.
nose up position.
- The 13 deg. mark on each wheel is opposite the
triangle on the center pedestal.
On the SD, on the F/CTL page:
- Wait until the PITCH TRIM indicator shows 13
deg. UP plus or minus 0.3 deg.
4. On the checkable shear-pin on the front face of
the THSA:
- Push and hold in the check button.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows XX in amber.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 28
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 37

@A330
SERVICE BULLETIN
ACTION
 RESULT
5. On the checkable shear-pin on the front face of
the THSA:
- Release the check button.
6. On the FLT CTL panel 212VU:
 On the FLT CTL panel 212VU:
- The OFF/R legend of the PRIM 2 comes on.
7. Do the steps 1. thru 6. again for the checkable
shear-pin on the rear face of the THSA.
Operational Test of the Checkable Shear-Pin with the PRIM 3
8.On the ECAM control panel:
- Push the F/CTL key.
On the SD:
- The F/CTL page comes into view.
9. On the FLT CTL panels 212VU:
- Push the PRIM 3 P/BSW.
NOTE
: When you push the PRIM 3
P/BSW, a trim setting will start.
You must wait until the trim setting
has completed before you continue
with step 10.
On the FLT CTL panel 212VU:
- The OFF/R legend of the PRIM 3 P/BSW goes
off.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator goes white.
On the center pedestal:
- The pitch-trim control wheel goes to 4 deg. UP.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows 4 deg. UP
plus or minus 0.4 deg.
10. On the center pedestal:
- Turn the pitch-trim control wheel to the 13 deg.
nose up position.
On the center pedestal:
- The 13 deg. mark on each wheel is opposite the
triangle on the center pedestal.
On the SD, on the F/CTL page:
- Wait until the PITCH TRIM indicator shows 13
deg. UP plus or minus 0.3 deg.
11. On the checkable shear-pin on the front face
of the THSA:
- Push and hold in the check button.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows XX in amber.
12. On the checkable shear-pin on the front face
of the THSA:
- Release the check button.
13. On the FLT CTL panel 212VU:
- Push the PRIM 3 P/BSW.
On the FLT CTL panel 212VU:
- The OFF/R legend of the PRIM 3 comes on.
14. Do the steps 8. thru 13. again for the
checkable shear-pin on the rear face of the THSA.
15. On the MCDU:
- Do the EFCS 1(2) GROUND SCANNING (Refer
to AMM Task 27-96-00-740-801)
On the MCDU:
- Make sure that there is no maintenance
message related to the THSA (1CS).
3
 Close-up
a
 Put the Aircraft to its Initial Configuration:
<1> Depressurize the aircraft hydraulic systems (Refer to AMM Task
29-00-00-864-801, AMM Task 29-00-00-864-802 and AMM Task
29-00-00-864-803).
<2> Do the EIS stop procedure (Refer to AMM Task 31-60-00-860-802).
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 29
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 38

@A330
SERVICE BULLETIN
<3> De-energize the aircraft electrical circuits (Refer to AMM Task
24-41-00-862-801).
**CONF ALL
E. CLOSE-UP
**CONF 001
(1) Subtask 273143-942-001-001 - Close-up.
Manpower Resources
Skills
 NON SPECIFIC
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Set the light switch to the OFF position and close the access door 312AR.
(c) Remove the warning notices from the cockpit.
(d) Restore the system and the aircr aft to normal operating condition.
(e) Remove the access platforms.
**CONF 002
(1) Subtask 273143-942-001-001 - Close-up.
Manpower Resources
Skills
 NON SPECIFIC
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Set the light switch to the OFF position and close the access door 312AR.
(c) Remove the warning notices from the cockpit.
(d) Restore the system and the aircr aft to normal operating condition.
(e) Remove the access platforms.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 30
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 39

@A330
SERVICE BULLETIN
Task 273143-831-802-001 - Modification - Additional Work
**CONF ALL
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE
IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL
OR INJURE PERSONS.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
LUBRIFICATION OF POST MOD THSA IS TO BE PERFORMED WITH AIMS
09-06-002 (CML 04-037).
Task Associated Data
**CONF 001
None
**CONF 002
Zone
120
 210
 310
Access
Door
 312AR
 811
 831
 841
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 31
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 40

@A330
SERVICE BULLETIN
Manpower
TOTAL MANHOURS
 5.00
ELAPSED TIME (HOURS)
 5.00
**CONF
 ALL
A. GENERAL
**CONF 001
None
**CONF 002
(1) Subtask 273143-839-002-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
(2) Subtask 273143-910-002-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-53, Page Block 001
Task 29-00-00-910-804
Elec. Std. Practices Manual (ESPM)
 20-33-00
(a) Clean the work area as necessary with Solvent General Purpose (Mat. No. 11-026)
and a Lint-Free Cotton Cloth (Mat. No. 19-003).
(b) Obey the hydraulic safety precautions (Refer to AMM Task 29-00-00-910-804).
(c) For identification of access panels (Refer to AMM 06-41-53, Page Block 001).
(d) Put blanking caps on disconnected hydraulic lines, open ports and electrical
connectors.
(e) For information on installation of Electrical Harness (Refer to ESPM 20-33-00).
**CONF
 ALL
B. PREPARATION
**CONF 001
None
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 32
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 41

@A330
SERVICE BULLETIN
**CONF 002
(1) Subtask 273143-941-002-001 - Job Set-up
Work Zones and Access Panels
Zone
 Access/Work location
210
 Access
 Door 831
, Door 841
310
 Access
 Door 312AR
120
 Access
 Door 811
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 27-40-00-866-801
Task 27-44-51-860-050
Task 29-00-00-864-804
Task 29-14-00-614-802
Task 29-14-00-614-803
(a) Make sure the aircraft is electrically grounded (Refer to AMM Task
12-34-24-860-802).
(b) Move the THS in zero degree position (Refer to AMM Task 27-40-00-866-801).
(c) Install the PITCH-TRIM CONTROL LOCKING (98F27401000000) on the pitch trim
control wheel (Refer to AMM Task 27-44-51-860-050).
(d) Depressurize the Blue and Yellow hydraulic systems(Refer to AMM Task
29-00-00-864-804).
(e) Depressurize the reservoir of the Blue and Yellow hydraulic systems (Refer to AMM
Task 29-14-00-614-802 and AMM Task 29-14-00-614-803).
(f) Put the warning notices in the cockpit, on the panel
 215VU and on the panel
990VU, to tell persons:
- not to start the APU.
- not to refuel the aircraft.
- not to pressurize the Blue and Yellow hydraulic systems.
- not to pressurize the reservoirs of the Blue and Yellow hydraulic systems.
- not to operate the THSA actuator.
(g) Put the access platform in position below the access door 811 to get access to the
avionics compartment.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 33
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 42

@A330
SERVICE BULLETIN
(h) Open, safety and tag these circuit breakers:
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1
)
722VU
 FCDC 2
 6CE2
 42 T
 (1
)
722VU
 FCSC 2
 10CE2
 37 T
 (1
)
722VU
 FCSC 2
 10CE2
 39 T
 (1
)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1
)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1
)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1
)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1
)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1
)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1
)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1
)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1
)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1
)
742VU
 FCDC 1
 6CE1
 64 E
 (1
)
742VU
 FCDC 1
 6CE1
 65 D
 (1
)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
(i) Put an access platform below the access door
 312AR.
(j) Open the access door
 312AR and set the light switch to the ON position.
(k) Install the MECHANICAL INPUT-RIGGING PIN (OU191067) on the mechanical
input of THS actuator and the ball-nut assembly (Refer to AMM Task
27-44-51-860-050).
(l) Put the TOOL-ZERO LOCATION THSA (OU191066) in position between the THS
actuator and the ball-nut assembly (Refer to AMM Task 27-44-51-860-050).
(m) Safety the upper end of the TOOL-ZERO LOCATION THSA (OU191066) to the
upper claw stop with a tie wrap.
(n) Put the FIXTURE-STRUT, HORIZONTAL STABILIZER PN 98A27407514004
(applicable pre mod 44205 D40465) or PN 98A27407514005 (applicable post mod
44205 D40465) in position and make sure that the THS is in zero degree position
(Refer to AMM Task 27-44-51-860-050).
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 34
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 43

@A330
SERVICE BULLETIN
**CONF
 ALL
C. PROCEDURE
**CONF 001
None
**CONF 002
(1) Subtask 273143-831-004-002 - Remove the Closing Plug from the Electrical
Harness 4515VB.
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
References
Fig. A-FBCAA
Removal of the Closing Plug from the
Electrical Harness / Connection of the
Electrical Harness to the THSA -
Additional Work
Sheet
 01
Sheet
 02
(a) Disassemble the electrical harness 4515VB from the supports of the THS front spar
(refer to
 Fig. A-FBCAA Sheet 01
 ).
2
 Screw
 Item (2
) Discard
2
 Washer
 Item (3
) Retain
4
 Clamp
 Item (4
) Discard
2
 Spacer
 Item (5
) Discard
1
 Clamp
 Item (6
) Discard
1
 Clamp
 Item (7
) Discard
(b) Remove the cable ties, item (9), and the support, item (8), to release the electrical
harness 4515VB.
2
 Cable tie
 Item (9
)
1
 Support
 Item (8
)
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 35
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 44

@A330
SERVICE BULLETIN
(c) Remove the closing plug, item (10), from the head of the electrical harness
4515VB.
1
 Closing Plug
 Item (10
)
(2) Subtask 273143-831-005- 002 - Connect the Electrical Harness 4515VB to the THSA.
Work Zones and Access Panels
Zone
 Access/Work location
310
 Access
 Door 312AR
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
Material necessary to do the job
Component COMPA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 NAS6703U4
 BOLT
References
Fig. A-FBCAA
Removal of the Closing Plug from the
Electrical Harness / Connection of the
Electrical Harness to the THSA -
Additional Work
Sheet
 01
Sheet
 02
(a) Install the electrical harness 4515VB.
1
 Attach the electrical harness 4515VB to the supports of the THS front spar
(Refer to
 Fig. A-FBCAA Sheet 02
 , detail E).
2
 Bolt
 NAS6703U4
 Item 11
2
 Washer
 Item (3
) Retained at
removal
2
 Attach the electrical harness 4515VB to the bracket of the THSA arm (Refer to
Fig. A-FBCAA Sheet 02
 , detail F).
- Remove and retain:
1
 Bolt
 Item (15
) Retain
1
 Washer
 Item (14
) Retain
1
 Clamp
 Item (13
) Retain
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 36
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 45

@A330
SERVICE BULLETIN
1
 Spacer
 Item (12
) Retain
- Install the harness 4515VB:
1
 Bolt
 Item (15
) Retained at
removal
1
 Washer
 Item (14
) Retained at
removal
1
 Clamp
 Item (13
) Retained at
removal
1
 Spacer
 Item (12
) Retained at
removal
(b) Remove the closing cap from the THSA CSP connector and connect the electrical
harness 4515VB.
**CONF
 ALL
D. TEST
**CONF 001
None
**CONF 002
(1) Subtask 273143-700-002-002 - Testing
Work Zones and Access Panels
Zone
 Access/Work location
120
 Access
 Door 811
210
 Access
 Door 831
, Door 841
310
 Access
 Door 312AR
Manpower Resources
Skills
 NON SPECIFIC
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 37
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 46

@A330
SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 Task 24-41-00-861-801
Task 24-41-00-862-801
Task 27-44-00-710-805
Task 27-44-51-710-801
Task 27-96-00-740-801
Task 29-00-00-863-801
Task 29-00-00-863-802
Task 29-00-00-863-803
Task 29-00-00-864-801
Task 29-00-00-864-802
Task 29-00-00-864-803
Task 31-60-00-860-801
Task 31-60-00-860-802
(a) Job Set-Up:
1
 Remove the safety clips and tags and close this (these) following circuit
breaker(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1
)
722VU
 FCDC 2
 6CE2
 42 T
 (1
)
722VU
 FCSC 2
 10CE2
 37 T
 (1
)
722VU
 FCSC 2
 10CE2
 39 T
 (1
)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1
)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1
)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1
)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1
)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1
)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1
)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1
)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1
)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1
)
742VU
 FCDC 1
 6CE1
 64 E
 (1
)
742VU
 FCDC 1
 6CE1
 65 D
 (1
)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 38
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 47

@A330
SERVICE BULLETIN
(b) Procedure:
- Do the Operational Check of THSA Checkable Shear-Pin, (Refer to AMM Task
27-44-51-710-801).
NOTE
: If the SB reference is not specified in the latest operator’s AMM
issue, do these steps:
1
WARNING
: PUT THE SAFETY DEVICES AND THE WARNING NOTICES
IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE
MOVEMENT OF COMPONENTS CAN KILL OR INJURE
PERSONS.
Job Set-Up:
a
WARNING
: MAKE SURE THAT THE PRIM 1 PUSHBUTTON
SWITCH IS PUSHED (OFF AND FAULT LEGENDS
OFF) BEFORE YOU PRESSURIZE THE HYDRAULIC
SYSTEM. IF THE PRIM 1 PUSHBUTTON SWITCH IS
RELEASED (OFF LEGEND ON) THE RUDDER CAN
MOVE AND CAUSE INJURY AND/OR DAMAGE.
WARNING
: MAKE SURE THAT THE PRIM 1 PUSHBUTTON
SWITCH IS PUSHED (OFF AND FAULT LEGENDS
OFF) BEFORE YOU PRESSURIZE THE HYDRAULIC
SYSTEM. IF THE PRIM 1 PUSHBUTTON SWITCH IS
RELEASED (OFF LEGEND ON) THE RUDDER CAN
MOVE AND CAUSE INJURY AND/OR DAMAGE.
Aircraft Maintenance configuration.
<1> Energize the aircraft electrical circuits (Refer to AMM Task
24-41-00-861-801).
<2> Do the EIS start procedure (EWD DU, SD DU only) (Refer to AMM
Task 31-60-00-860-801).
<3> Pressurize the aircraft hydraulic systems (Refer to AMM Task
29-00-00-863-801, AMM Task 29-00-00-863-802 and AMM Task
29-00-00-863-803).
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 39
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 48

@A330
SERVICE BULLETIN
<4> Put the WARNING NOTICE(S) in position to tell persons that the
trimmable horizontal stabilizer (THS) is in operation.
<5> On the FLT CTL section of the overhead panel
 241VU, make sure
that the PRIM 1 and SEC 1 P/BSWs are released (OFF legends are
on).
<6> On the FLT CTL section of the overhead panel
 212VU, make sure
that the PRIM 2, PRIM 3 and SEC 2 P/BSWs are released (OFF
legends are on).
b
 On the ECAM control panel, push the C/B key (on the SD the C/B page
comes into view). Make sure that the SD does not show this (these)
circuit breaker(s) :
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
721VU
 FCPC3 STBY COM
 7CE6
 20 R
721VU
 FCPC3 STBY MON
 7CE5
 19 R
722VU
 FCDC 2
 6CE2
 40 T
 (1
)
722VU
 FCDC 2
 6CE2
 42 T
 (1
)
722VU
 FCSC 2
 10CE2
 37 T
 (1
)
722VU
 FCSC 2
 10CE2
 39 T
 (1
)
722VU
 THS ACTR MOT 3
 5CS3
 44 V
722VU
 THS ACTR MOT2 NORM
 5CS2
 43 V
722VU
 FCPC 3
 7CE3
 42 V
722VU
 FCPC 2 NORM
 7CE2
 41 V
722VU
 FCPC 3
 7CE4
 38 V
742VU
 FCSC 1 NORM
 10CE1
 67 C
 (1
)
742VU
 FCSC 1 NORM
 10CE1
 70 C
 (1
)
742VU
 FCPC 1 NORM
 7CE1
 66 C
 (1
)
742VU
 FCPC 1 NORM
 7CE1
 69 C
 (1
)
742VU
 FCSC 1 STBY
 9CE
 75 G
 (1
)
742VU
 FCSC 1 STBY
 9CE
 77 G
 (1
)
742VU
 FCPC 1 STBY
 11CE
 67 K
 (1
)
742VU
 FCPC 1 STBY
 11CE
 69 K
 (1
)
742VU
 THS ACTR MOT 1
 5CS1
 77 L
742VU
 FCDC 1
 6CE1
 76 L
 (1
)
742VU
 FCDC 1
 6CE1
 64 E
 (1
)
742VU
 FCDC 1
 6CE1
 65 D
 (1
)
NOTE
 (1)
: The location of the CB depends on the A/C configuration.
2
 Procedure
a
 Operational Test of the Checkable Shear-Pin.
NOTE
: Two persons are necessary to do this procedure:
- One person at the THSA to push the checkable
shear-pin check button.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 40
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 49

@A330
SERVICE BULLETIN
- One person in the cockpit to read the messages,
push the P/BSW’s and turn the pitch-trim control
wheel.
NOTE
: You must do this procedure for one checkable shear-pin,
then you must do the test again for the other checkable
shear-pin.
ACTION
 RESULT
Operational Test of the Checkable Shear-Pin with the PRIM 2
1. On the ECAM control panel:
- Push the F/CTL key.
On the SD:
- The F/CTL page comes into view.
2. On the FLT CTL panels
 212VU:
- Push the PRIM 2 P/BSW.
NOTE
: When you push the PRIM 2
P/BSW, a trim setting will start.
You must wait until the trim setting
has completed before you continue
with step 3.
On the FLT CTL panels
 212VU:
- The OFF/R legend of the PRIM 2 P/BSW goes
off.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator goes white.
On the center pedestal:
- The pitch-trim control wheel goes to 4 deg. UP.
- On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows 4 deg. UP
plus or minus 0.4 deg.
3. On the center pedestal:
- Turn the pitch-trim control wheel to the 13 deg.
nose up position.
- The 13 deg. mark on each wheel is opposite the
triangle on the center pedestal.
On the SD, on the F/CTL page:
- Wait until the PITCH TRIM indicator shows 13
deg. UP plus or minus 0.3 deg.
4. On the checkable shear-pin on the front face of
the THSA:
- Push and hold in the check button.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows XX in amber.
5. On the checkable shear-pin on the front face of
the THSA:
- Release the check button.
6. On the FLT CTL panel
 212VU:
 On the FLT CTL panel
 212VU:
- The OFF/R legend of the PRIM 2 comes on.
7. Do the steps 1. thru 6. again for the checkable
shear-pin on the rear face of the THSA.
Operational Test of the Checkable Shear-Pin with the PRIM 3
8.On the ECAM control panel:
- Push the F/CTL key.
On the SD:
- The F/CTL page comes into view.
9. On the FLT CTL panels
 212VU:
- Push the PRIM 3 P/BSW.
NOTE
: When you push the PRIM 3
P/BSW, a trim setting will start.
You must wait until the trim setting
has completed before you continue
with step 10.
On the FLT CTL panel
 212VU:
- The OFF/R legend of the PRIM 3 P/BSW goes
off.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator goes white.
On the center pedestal:
- The pitch-trim control wheel goes to 4 deg. UP.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows 4 deg. UP
plus or minus 0.4 deg.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 41
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 50

@A330
SERVICE BULLETIN
ACTION
 RESULT
10. On the center pedestal:
- Turn the pitch-trim control wheel to the 13 deg.
nose up position.
On the center pedestal:
- The 13 deg. mark on each wheel is opposite the
triangle on the center pedestal.
On the SD, on the F/CTL page:
- Wait until the PITCH TRIM indicator shows 13
deg. UP plus or minus 0.3 deg.
11. On the checkable shear-pin on the front face
of the THSA:
- Push and hold in the check button.
On the SD, on the F/CTL page:
- The PITCH TRIM indicator shows XX in amber.
12. On the checkable shear-pin on the front face
of the THSA:
- Release the check button.
13. On the FLT CTL panel
 212VU:
- Push the PRIM 3 P/BSW.
On the FLT CTL panel
 212VU:
- The OFF/R legend of the PRIM 3 comes on.
14. Do the steps 8. thru 13. again for the
checkable shear-pin on the rear face of the THSA.
15. On the MCDU:
- Do the EFCS 1(2) GROUND SCANNING (Refer
to AMM Task 27-96-00-740-801)
On the MCDU:
- Make sure that there is no maintenance
message related to the THSA (1CS).
3
 Close-up
a
 Put the Aircraft to its Initial Configuration:
<1> Depressurize the aircraft hydraulic systems (Refer to AMM Task
29-00-00-864-801, AMM Task 29-00-00-864-802 and AMM Task
29-00-00-864-803).
<2> Do the EIS stop procedure (Refer to AMM Task 31-60-00-860-802).
<3> De-energize the aircraft electrical circuits (Refer to AMM Task
24-41-00-862-801).
**CONF
 ALL
E. CLOSE-UP
**CONF 001
None
**CONF 002
(1) Subtask 273143-942-003-002 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 42
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 51

@A330
SERVICE BULLETIN
(b) Set the light switch to the OFF position and close the access door
 312AR.
(c) Remove the warning notices from the cockpit.
(d) Restore the system and the aircr aft to normal operating condition.
(e) Remove the access platforms.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 43
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 52

@A330
SERVICE BULLETIN
**CONF 001
ACCESS
PANEL
BEFORE
Z310
A
312AR
FR80
FR87
B C
G_SB_273143_5_BAAA_01_00
AFTER
CSP
CONNECTOR
(1) 1
A
B C
Figure A-FBAAA - Sheet 01
Modification of the Trimmable Horizontal Stabilizer Actuator
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 44
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 53

@A330
SERVICE BULLETIN
**CONF 002
ACCESS
PANEL
BEFORE
Z310
A
312AR
FR80
FR87
B C
AFTER
CSP
CONNECTOR
(1) 1
A
B C
G_SB_273143_5_BAAB_01_00
Figure A-FBAAB - Sheet 01
Modification of the Trimmable Horizontal Stabilizer Actuator
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 45
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 54

@A330
SERVICE BULLETIN
**CONF 002
BEFORE
Z319
A
4515VB
(4)
(6)
(4)
(7)
(9)
(8)
(9)
(2)
(3)
(4)
(2)
(3)
(4)
(5)
(5)
(10)
B D
C
A
B C
G_SB_273143_5_BBAA_01_00
Figure A-FBBAA - Sheet 01
Removal of the Closing Plug from the Electrical Harness / Connection of the Electrical Harness
to the THSA
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 46
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 55

@A330
SERVICE BULLETIN
**CONF 002
AFTER
4515VB
(13) (14)
(15)
(12)
(3)
11
(3)
11
4515VB
F
E
D
E
F
G_SB_273143_5_BBAA_02_00
Figure A-FBBAA - Sheet 02
Removal of the Closing Plug from the Electrical Harness / Connection of the Electrical Harness to the
THSA
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 47
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 56

@A330
SERVICE BULLETIN
**CONF 002
BEFORE
Z319
A
4515VB
(4)
(6)
(4)
(7)
(9)
(8)
(9)
(2)
(3)
(4)
(2)
(3)
(4)
(5)
(5)
(10)
B D
C
A
B C
G_SB_273143_5_BCAA_01_00
Figure A-FBCAA - Sheet 01
Removal of the Closing Plug from the Electrical Harness / Connection of the Electrical Harness
to the THSA - Additional Work
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 48
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 57

@A330
SERVICE BULLETIN
**CONF 002
AFTER
4515VB
(13) (14)
(15)
(12)
(3)
11
(3)
11
4515VB
F
E
D
E
F
G_SB_273143_5_BCAA_02_00
Figure A-FBCAA - Sheet 02
Removal of the Closing Plug from the Electrical Harness / Connection of the Electrical Harness to the
THSA - Additional Work
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 49
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 58

@A330
SERVICE BULLETIN
REPORTING SHEET
TITLE: FLIGHT CONTROLS - TRIMMABLE HORIZONTAL STABILIZER -
INTRODUCE MODIFIED THSA (P/N 47147-700).
MODIFICATION No.: 54881D46193
Please complete the appropriate item (A or B):
A - SB WILL BE
 embodied YES/NO (if NO please comment)
If YES, aircraft concer ned (as per SB effectivity by default) and planned dates (month/year) of
embodiment:
B - SB HAS BEEN
 embodied on aircraft:
Operator comments:
From Airline:
Name/Title:
Signature: Date:
If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to
next normal revision or prior to SB embodiment, please indicate required service(s):
Either: Modification Operational Impact (MOI), if available YES/NO
Or : Intermediate revision YES/NO
Important Information:
 This SB will only be incorporated in your maintenance and operational
documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With
the next feasible revision, this will result in
- Updating of maintenance documentation to show pre and post SB data.
- Updating of maintenance and operational documentation to show post SB data after embodiment.
If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically
include them in the manual revisions. Refer to SIL 00-037 for detailed information.
Please return this completed sheet to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn: SDC32 Technical Data and Documentation Services
F A X :( + 3 3 )56 19 32 80 6
e-mail: sb.reporting@airbus.com
or via your Resident Customer Support Office.
Alternatively, SB lists via letters or fax are also accepted.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 59

@A330
SERVICE BULLETIN
QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data
that you provide us will be used to analyse areas of difficulties and to take corrective action to further
improve the quality of our Service Bulletins.
We thank you for the time you have taken in completing this form.
(Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4321
- Quality rating of the Accomplishment Instructions 4321
- Quality rating of the Illustrations 4321
- Is this SB easy to understand ? Y/N
If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a
short description of the issue.
Planning Material Instructions
X Effectivity X Kit content X Preparation
X Reason X List of Materials Operator Supplied X Mod/Inspection
X Manpower X Industry support X Test
X References X Re-identification X Close-Up
X Publication X Tooling X Illustrations
Comments:
Operator: Date:
Name/Title:
Please return this form to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn : SEM4 Service Bulletins Management
F A X:( 3 3 )56 19 34 25 1
Or via your Resident Customer Support Office.
DATE: Feb 21/12 SERVICE BULLETIN No.: A330-27-3143
REVISION No.: 01 - Jul 10/12 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

---
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.