ALERT OPERATORS TRANSMISSION

- ALERT OPERATORS TRANSMISSION SUBJECT: ATA 55

- RUDDER SIDE PANEL INSPECTION ALONG THE Z-PROFILE OUR REF.: A55W002-12 dated 13 Dec 2012 1. AIRCRAFTAFFECTED All A300-600 and A310 aircraft in pre modification 8827 configuration, with a rudder assembly Part Number (PN) startingwith A55471500. The inspection has to be performed only ifthe last inspection as per ref.1or 2was done offaircraft or ifthe rudder has been removed since then for any reason. 2. REFERENCED DOCUMENTATION 2.1APPENDIX Appendix 1: Inspection flow chart 2.2 REFERENCES Ref.1: Service Bulletin SB A310-55-2044 dated Jul 23/07 Ref.2: service Bulletin SB A300-55-6043 dated Dec 03/07 Ref.3: NTM 55-40-02 Part 4 (Ultrasonic inspection) Ref.4. NTM 51-10-26 Part 7 (ELCH inspection) Ref.5: NTM 51-10-19 Part 5 (woodpecker inspection)· Ref.6: NTM 51-10-03 Part 5 (Tap test inspection) Ref.?: AMM 27-21-21 PB401 (Rudder removal/installation) dated Ref.8: NTM 55-40-09 3. REASON 3.1 FACTS Part 7, Figure 701 (Inspection Area) prior to Dec 2012

Affected rudders are subject to service Bulletins ref.1 and 2introducing a specific repetitive ultrasonic (UT) inspection along the rudder panel front and bottom edge. This inspection is intended to identify possible areas ofdisbanding on the internal surface ofthe rudder side panels. one A310 rudder with rudder assembly Part Number (P/N) startingwith A55471500 has been recently identifiedwith large inner skin disband damage. This rudder was inspected as per service Bulletin ref.1 at 21028 accumulated Flight Cycles (FC) with nil findings. 986 Flight cycles (FC) after this inspection subject rudder was sent toAirbus facilities for a specific repair outside the scope ofthe inspection ref.1. The damage was detected during the incoming inspection. An investigation revealed that the most probable cause ofthe large honeycomb core debonding 1nitiationwas a blunt impactwith no visible damage from outside during rudder handling (removal/installation). The rudder involved in this eventwas part number (PN) A55471500 series, which is sensitive to damage in the area ofthe z-profile during rudder handling. An impact damage might grow with difference ofpressure associated to ground-air-ground cycles. 3.2 CONSEQUENCES Page 1AOT_A55W002_12_00[1].txt An inner skin disbanding ofthe detected size degrades the structural integrity of the rudder. Tests performed in previous rudder showed a rapid propagation ofdamage during artificial pressure cycling. 3.3AIM The aim ofthisAOT is to verify the structural integrityofthe rudder by means of one time ultrasonic (UT) inspection. The inspection must be repeated before next flight after any further re-installation ofthe rudder onto an aircraft until issuance of revisedAMM task ref.?. This inspection will prevent undetected damage introduced during rudder ground handling. 4. SHORTTERM ACTION 4.1 PLANNING AND MANPOWER 4.1.1ACCOMPLISHMENT TIMESCALE The inspections described in paragraph 4.2 must be performedwithin 3months from the reception date ofthisAOT. 4.1.2 MANPOWER For A310 aircraft, refer to SB ref.1 paragraph 1.G. ForA300-600 aircraft, refer to SB ref.2 paragraph 1.G. 4.2 DESCRIPTION 4.2.1ACCESS Inspection must be performedwith the rudder installed on the aircraft. ForA310 aircraft, refer to SB ref.1paragraph 3.A.(1). For A300-600 aircraft, refer to SB ref.2 paragraph 3.A.(1). 4.2.2 INSPECTION REQUIREMENTS Refer to flowchart appendix 1 for an overviewofthe inspection requirements. Identifythe rudder assembly part number and serial number beforeyou start the inspection. Ifit is not possible, contactAirbus for identification advice. Ifinstalled rudder assembly part number is not startingwith A55471500, no further action is required as per thisAOT. Rudder shells must be inspected in areas defined in:

- Figure 3of SB ref.1, for A310 aircraft.

- Figure 3of SB ref.2, for A300-600 aircraft. Perform an ultrasonic (UT) inspection in accordancewith ref.3 in the inspection area. Ifcase offinding, the UT indication shall be verified to differentiate disband from other possible damages. This differentiation should be done using both methods:

- ELCH in accordancewith ref.4 for detection ofexternal and internal disband. -woodpecker in accordancewith ref.S orTap test in accordancewith ref.6 for detection ofexternal disband. Page 2AOT_A55W002_12_00[1].txt Note: In case ofUT indication in booster area (see ref.8), report toAirbus to get further instructions before next flight. Iffinding is confirmed as disbond damage, refer to Para. 4.2.3. Iffinding is confirmed as other type ofdamage (e.g. liquid ingress), check applicable SRM chapter for allowable damage. The inspectionmust be repeated before next flight after any further re-installation ofthe rudder onto an aircraft until issuance of revisedAMM task ref.?. 4.2.3 FINDINGS In case ofdisbond withwidth 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. -ForA310 aircraft, refer to SB ref.1paragraph 3.C.(1).

- For A300-600 aircraft, refer to SB ref.2 paragraph 3.C.(1). Then, contactAirbuswithin 10 days from the date ofthe inspection with a detailed damage report to get permanent repair instructions. The permanent repair shall be performedwithin 100FC from inspection date. In case ofdisbond withwidth greater than 50 mm (1.968 in.) orwith length greater than 150 mm (5.905 in.), contactAirbus 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.3.

- Inspection equipment for ELCH as per ref.4.

- Inspection equipment for woodpecker test as per ref.5.

- Inspection equipment for Tap test as per ref.6. 5. FURTHER INFORMATION 5.1 FOLLOW-UP PLAN The AMM task ref.? will be revised to include this UT inspection after each re-installation ofthe rudder onto an aircraft. The revisedAMM is expected to be issued on the second quarter of 2013. Page 3AOT_A55W002_12_00[1].txt 5
.2 IMPACTED DOCUMENTATION AMM 27-21-21 PB 401 6. AOTAPPROVAL The technical content ofthis document is approved under the authority ofDOA nr. EASA.21J.031. 7. REPORTING/ACKNOWLEDGEMENT Operators are requested to acknowledge receipt ofthis 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 Questions about this AOT and inspection resultswith orwithout findings are to be sent toAirbus customer services engineering as soon as possible, after theAOT 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 VICE PRESIDENT ENGINEERING SUPPORT PROGRAMME CUSTOMER SERVICES

Page 4 Philippe BOUCHERAT VICE PRESIDENT A300/A310 CUSTOMER SERVICESInspection Flowchart AOT ref.: A55W002-12

Rudder PN A55471500 series re - installed onto aircraft.

Within 3 months from AOT reception, perform UT inspection with rudder installed in aircraft as per as per N T M 55-40-02 Part 4 in I

area defined in SB A31 0-55-2044 Fig. 3 or SB A300-55-6043 Fig.3

yes r---- no I

Repeat the inspection before next flight aft; any I

·-- · · · ·· · · · ····· >j

further re-installation of the rudder on t o an aircraft i

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until issuance of revised AMM 27-21-21 P8401 1

Disband confirmation requested using both methods:

- ELCH NTM 51-1 0-26 Part 7 for external and internal disband.

-

Woodpecker NTM 51-1 0-19 Part 5 or Tap test NTM 51-1 0-03 Part 5 for external disband

no **--** -- ) [ Check applicable SRM chapter for allowable damage

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