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. AIRCRAFT AFFECTED 

All A300-600 and A310 aircraft in pre modification 8827 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 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 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 disbanding 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 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 to Airbus facilities for a specific repair outside the scope of the 

inspection ref.1. The damage was detected during the incoming inspection. 

An investigation revealed that the most probable cause of the large honeycomb core 

debonding 1nitiation 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 

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AOT_A55W002_12_00[1].txt 

An inner skin disbanding of the detected size degrades the structural integrity of the rudder. Tests performed in previous rudder 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.?. 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 A310 aircraft, refer to SB ref.1 paragraph 1.G. 

For A300-600 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 A310 aircraft, refer to SB ref.1 paragraph 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 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 3 of SB ref.1, for A310 aircraft. - Figure 3 of SB ref.2, for A300-600 aircraft. 

Perform an ultrasonic (UT) inspection in accordance with ref.3 in the inspection 

area. 

If case of finding, the UT indication shall be verified to differentiate disband from other possible damages. This differentiation should be done using both methods: - ELCH in accordance with ref.4 for detection of external and internal disband. 

-woodpecker in accordance with ref.S or Tap test in accordance with ref.6 for detection of external disband. 

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AOT_A55W002_12_00[1].txt 

Note: In case of UT indication in booster area (see ref.8), 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), check 

applicable SRM chapter for allowable damage. 

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.?. 

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 A310 aircraft, refer to SB ref.1 paragraph 3.C.(1). - For A300-600 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 

Mail to: 

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 of the rudder onto an aircraft. 

The revised AMM is expected to be issued on the second quarter of 2013. 

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AOT_A55W002_12_00[1].txt 

5. 2 IMPACTED DOCUMENTATION 

AMM 27-21-21 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 

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 

VICE PRESIDENT ENGINEERING SUPPORT 

PROGRAMME 

CUSTOMER SERVICES 

Page 4 

Philippe BOUCHERAT 

VICE PRESIDENT A300/A310 

CUSTOMER SERVICES 
Inspection 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 NTM 55-

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 nex

·-- ····· · · · ·····>j further re-installation of the rudde

l until issuance of revised AMM 27

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 allowab

1 

k~ 

ysbond size 

-

W~50mm and L~150mm 

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