ALERT OPERATORS TRANSMISSION - ALERT OPERATORS TRANSMISSION

SUBJECT: ATA 55 - RUDDER SIDE PANEL INSPECTION ALONG THE Z-PROFILE OUR REF.: A55L001-12 dated 20 Dec 2012
1. AIRCRAFT AFFECTED All A330 and A340 aircraft in pre modification 41800 configuration, with a rudder assembly Part Number (PN) starting with A55471500. The inspection has to be performed only if the last inspection as per ref.1 or 2 was done off aircraft or if the rudder has been removed since then for any reason.

2. REFERENCED DOCUMENTATION
2.1 APPENDIX Appendix 1: Inspection flow chart
2.2 REFERENCES Ref.1: Service Bulletin SB A330-55-3038 dated Nov 07/07 Ref.2: Service Bulletin SB A340-55-4034 dated Nov 07/07 Ref.3: Service Bulletin SB A310-55-2044 dated Dec 03/07 Ref.4: NTM Task 55-40-02-270-801 (Ultrasonic inspection) Ref.5. NTM Task 51-10-26-220-801 (ELCH inspection) Ref.6: NTM Task 51-10-19-280-801 (Woodpecker inspection) Ref.7: NTM Task 51-10-03-280-801 (Tap test inspection) Ref.8: AMM 27-21-41 PB 401 (Rudder removal/installation) prior to Dec 2012 Ref.9: NTM Figure 55-40-09-991-012-A (Rudder inspection zones)

3. REASON
3.1 FACTS Affected rudders are subject to Service Bulletins ref.1 and 2 introducing a specific repetitive ultrasonic (UT) inspection along the rudder panel front and bottom edge. This inspection is intended to identify possible areas of disbonding on the internal surface of the rudder side panels. One A310 rudder with rudder assembly Part Number (P/N) starting with A55471500 has been recently identified with large inner skin disbond damage. This rudder was inspected as per Service Bulletin ref.3 at 21028 accumulated Flight Cycles (FC) with nil findings. 986 Flight Cycles (FC) after this inspection subject rudder was sent to Airbus facilities for a specific repair outside the scope of the inspection ref.3. The damage was detected during the incoming inspection. An investigation revealed that the most probable cause of the large honeycomb core debonding initiation was a blunt impact with no visible damage from outside during rudder handling (removal/installation).The rudder involved in this event was part number (PN) A55471500 series, which is sensitive to damage in the area of the Z-profile during rudder handling. An impact damage might grow with difference of pressure associated to ground air ground cycles. 3.2 CONSEQUENCES An inner skin disbonding of the detected size degrades the structural integrity of the rudder. Tests performed on rudders showed a rapid propagation of damage during artificial pressure cycling.

3.3 AIM The aim of this AOT is to verify the structural integrity of the rudder by means of one time ultrasonic (UT) inspection. The inspection must be repeated before next flight after any further re-installation of the rudder onto an aircraft until issuance of revised AMM task ref.8. This inspection will prevent undetected damage introduced during rudder ground handling.

4. SHORT TERM ACTION
4.1 PLANNING AND MANPOWER
4.1.1 ACCOMPLISHMENT TIMESCALE The inspections described in paragraph 4.2 must be performed within 3 months from the reception date of this AOT.

4.1.2 MANPOWER For A330 aircraft, refer to SB ref.1 paragraph 1.G. For A340 aircraft, refer to SB ref.2 paragraph 1.G.

4.2 DESCRIPTION
4.2.1 ACCESS Inspection must be performed with the rudder installed on the aircraft. For A330 aircraft, refer to SB ref.1 paragraph 3.A.(1). For A340 aircraft, refer to SB ref.2 paragraph 3.A.(1).
4.2.2 INSPECTION REQUIREMENTS Refer to flowchart appendix 1 for an overview of the inspection requirements. Identify the rudder assembly part number and serial number before you start the inspection. If it is not possible, contact Airbus for identification advice. If installed rudder assembly part number is not starting with A55471500, no further action is required as per this AOT. Rudder shells must be inspected in areas defined in:- Figure 2 of SB ref.1, for A330 aircraft. - Figure 2 of SB ref.2, for A340 aircraft. Perform an ultrasonic (UT) inspection in accordance with ref.4 in the inspection area. If case of finding, the UT indication shall be verified to differentiate disbond damage from other possible damage. This differentiation should be done using both methods: - ELCH in accordance with ref.5 for detection of external/internal disbond. - Woodpecker in accordance with ref.6 or Tap test in accordance with ref.7 for detection of external disbond. Note: In case of UT indication in booster area (see ref.9), report to Airbus to get further instructions before next flight. If finding is confirmed as disbond damage, refer to Para. 4.2.3. If finding is confirmed as other type of damage (e.g. liquid ingress), contact Airbus before next flight with a detailed damage report to get further instructions. The inspection must be repeated before next flight after any further re-installation of the rudder onto an aircraft until issuance of revised AMM task ref.8.

4.2.3 FINDINGS In case of disbond with width equal or less than 50 mm (1.968 in.) and with length equal or less than 150 mm (5.905 in.), vent the core before next flight. - For A330 aircraft, refer to SB ref.1 paragraph 3.C.(1). - For A340 aircraft, refer to SB ref.2 paragraph 3.C.(1). Then, contact Airbus within 10 days from the date of the inspection with a detailed damage report to get permanent repair instructions. The permanent repair shall be performed within 100FC from inspection date. In case of disbond with width greater than 50 mm (1.968 in.) or with length greater than 150 mm (5.905 in.), contact Airbus before next flight with a detailed damage report to get further instructions. Detailed damage report has to be sent to the following address: Repair Engineering (SEER1/SEER2/SEER3) Customer Services Fax: +33 (0)5 61 93 28 73 Mailto: region1.StructureRepairSupport@airbus.com region2.StructureRepairSupport@airbus.com region3.StructureRepairSupport@airbus.com Or for AOG request AIRTAC (Airbus Technical AOG Center) Customer Services Phone: +33 (0)5 61 93 34 00 Fax: +33 (0)5 61 93 35 00 Mailto: airtac@airbus.com

4.3 SPARES AND TOOLING- Inspection equipment for Ultrasonic inspection as per ref.4. - Inspection equipment for ELCH as per ref.5. - Inspection equipment for Woodpecker test as per ref.6. - Inspection equipment for Tap test as per ref.7.

5. FURTHER INFORMATION
5.1 FOLLOW-UP PLAN The AMM task ref.8 will be revised to include this UT inspection requirement after each re-installation of the rudder onto an aircraft. The revised AMM is expected to be issued on the second quarter of 2013.

5.2 IMPACTED DOCUMENTATION
AMM 27-21-41 PB 401

6. AOT APPROVAL The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.

7. REPORTING / ACKNOWLEDGEMENT Operators are requested to acknowledge receipt of this AOT within 48 hours after receipt to: Cecile BORDES SEES E-mail: Cecile.bordes@airbus.com Fax number: +33 (0) 5.61.93.36.14 This acknowledgement can be made through the airbus field service office when available. Questions about this AOT and inspection results with or without findings are to be sent to Airbus Customer Services engineering as soon as possible, after the AOT application, to the attention of: Paloma LLEDIN BARBANCHO - SEES1 Customer Services Phone: +33 (0)5 67 19 10 84 Fax: +33 (0)5 61 93 36 14 Mailto: paloma.lledin@airbus.com Best Regards, Jean-Luc MOUYSSET Philippe GOURDON VICE PRESIDENT ENGINEERING SUPPORT VICE PRESIDENT A330/A340 PROGRAMME CUSTOMER SERVICES CUSTOMER SERVICES