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This text is OCR from a scan. OCR can misread letters and numbers. © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2010-0281; AD 2010-16-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
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~9719384.txt
ALL OPERATORS TELEX - ALL OPERATORS TELEX SUBJECT: A31O - ATA S0-40 - INSPECTION OF RUDDER SIDE SHELLS FOR
POTENTIAL SKIN TO HONEYCOMB DISBOND OUR REF: AOT A310-55A2048 Rev 02 dated 12 OCT 09 OUR PREVIOUS REF: AOT A310-55A2048 Rev 01 dated 08 July 09 AOT A310-55A2048 Rev 00 dated 11 May 09
0. REASON FOR REVISION This AOT has been revised to:
- Introduce an ultrasonic inspection in the reinforced areas of the rudders. This ultrasonic inspection replaces the thermography inspection required by AOT A310-55A2048 Rev. 01 and as defined ir the specific Technical Dispositions for reinforced areas location . The thermography inspection requirements remain applicable ir areas as defined in the specific Technical Dispositions for location D, F, G, M and N.
- Introduce minor changes in Technical TD/K4/S1/27583/2009, now revised
- References to the specific Technical Dispositions for location A have been updated
- References to the specific Technical Dispositions for the "other areas" at location D, F, G, H, J, K, L, M and N have been included in appendix A.
- Titles of Dimensions of inspection drawings have been revised (page 15) .
- Reflect that the ELCh inspection at Trailing Edge area has to be repeated twice at intervals not exceeding 4500 FC, but no less than 4000 FC since last inspection.
No additional work is required for rudders that have been inspected through AOT A310-55A2048 Rev.01 dated 08 July 09, except those on which temporary option II or permanent vacuum loss hole restoration has been performed according to the specific Technical Dispositions at Location A: In this case, an additional Ultrasonic inspection within 4500 FC from restoration date is required.
The revised paragraphs are indicated between **BEG.REV** and **END. REV**.
1. AIRCRAFT AFFECTED All A310 aircraft equipped with rudders having the Serial Numbers (SN) listed in Technical Disposition ref. TD/K4/S1/27583/2009 issue E Table -, and having a honeycomb core density of 24 kg/m3 (rudders ticked "x" in column "24kg core or All A310 aircraft equipped with rudders having the Serial Numbers (SN) listed in Țechnical Disposition ref. TD/K4/S1/27583/2009 issue E Table 1, and having accumulated 13000 FC or more since their first installation on aircraft at receipt date of this AOT.
Note: Affected rudders listed in Technical Disposition ref.
TD/K4/S1/27583/2009 issue E Table 1, having a honeycomb core density greater than 24kg/m3 and having accumulated less than 13000 FC at receipt date of this AOT, are also to be inspected according to the
~9719384.txt AOT's instructions. However for these rudders the accomplishment timescale given paragraph 4.1.1 has to be considered from the date when the 13000 FC threshold is reached.
**BEG. REV** The tollowing rudders that have been inspected through the sampling campaign, inspected at trailing edge location, in accordance with this AOT.
SN HF-1059 SN HF-1087 must be perred within 450 ic from despisent or the sampling inspection, and repeated one time at an interval not exceeding 4500 FC, but no less than 4000 FC since last inspection.
**END. REV** Insation er delive demen are trive a fatal th another aircraft, responsibility of the operator to apply the required instructions contained in this AOT to the new aircraft.
If the cross-reference Rudder SN/ Aircraft MSN given ir TD/K4/S1/27583/2009 issue E Table 1 does not reflect the current status or if the identification plate is missing, contact Airbus.
2. REFERENCED DOCUMENTATION **BEG. REV** REF.1: OIT 999.0092/08: ATA55 - Rudder side shell Skin disbonding REF.2: A310 SRM 55-41-12 Fig. 1 item 10 & 15 REF.3: Technical Disposition ref. .TD/K4/S1/27583/2009 issue E REF.4. NTM 51-10-26 Part 7 (ELCh inspection) REF 5: NTM 51-10-28 Part 7 (Vacuum Loss inspection) REF 6: NTM 55-40-02 Part 10 (Thermography inspection) REF 7: NT 51-10-19 Part 5 (Tap test inspection) REF 8: NTM 51-10-24 Part 4 - NTM Temporary Revision TR 51-006 based on June 09 revision (Ultrasonic inspection).
**END. REV**
3. REASON
3.1 BACKGROUND A deformation was visually detected on the rudder side shell of an A319 and an A321 in-service aircraft. Both rudders were sent to Airbus facilities for further analysis. A review of production records revealed that the deformations reported on both rudders corresponded to areas that had been reworked in production.
The conclusion of the investigation is that the disbonding most likely occurred as a consequence ot curina rework of the inner skin in production.
outside the autoclave.
such hot curing reworks were also performed on some A310 rudders Operators were informed thru OIT REF. 1 dispatched in November 2008 and revised in March 2009.
3.2 AIM Page 2
~9719384.txt For rudders that have been reworked in production with similar hot curing process, this AOT calls for:
- a one-time Vacuum Loss inspection at rudder shell reinforced areas
- a three(3)-times repetitive Elasticity Laminate Checker (ELCh) inspection at rudder shell trailing edge area
- a repetitive ELCh inspection in other rudder shell areas; until a Vacuum Loss inspection is performed (considered as the terminating
4. SHORT TERM ACTION
4.1 PLANNING AND MANPOWER This AOT is subject to an Airbus Monitored Retrofit Campaign. For logistic purposes please provide in advance the inspection planning.
Your focal point for the planning and the logistics is:
DIETZ, SEOT2 Customer Services Phone: +33 (0) 5 67 19 14 22 Fax: +33 (0) 5 61 93 27 45 Mailto: wera.dietz@airbus.com
4.1.1 ACCOMPLISHMENT TIMESCALE Accomplishment timescale depends on the locations of the areas to be inspected, which are fully described in Technical Disposition ref.
TD/K4/S1/27583/2009 issue E.
4.1.1.1 FOR REINFORCED AREAS The one-time Vacuum Loss inspection described in paragraph 4.2.2.1 must be performed within 8 months from the receipt date of this AOT.
**BEG.REV**
4.1.1.2 FOR TRAILING EDGE AREA The ELCh inspection described in paragraph 4.2.2.2 must be pertormed within 24 months from the receipt date of this AOT, and repeated twice at intervals not exceeding 4500 FC, but no less than 4000 FC since last fos lowing the third inspection without findings, no further action is required in the trailing edge area.
**END. REV**
4.1.1.3 FOR OTHER AREAS (LOWER RIB/UPPER EDGE/LEADING EDGE/OTHER
LOCATIONS) The repetitive ELCh inspection described in paragraph 4.2.2.3.A. must be performed:
- within 8 months from the receipt date of this AOT
- then, repeated at intervals not exceeding 8 months accomplishment of the terminating one-time Vacuum Loss inspection mentioned in paragraph 4.2.2.3.B., that must be pertormec within 24 months from the receipt date of this AOT.
Accomplishment of this terminating one-time inspection cancels the repetitive ELCh inspection requirements described in paragraph
4.2.2.3.A.
If the vacuum loss inspection is performed within 8 months from the
~9719384. txt receipt date of the AOT, no ELCh inspection is required before or simultaneously.
4.1.2 MANPOWER The manpower estimates given below are based on the direct labour to do the work. These estimates assume that the work will be done by experienced personnel. They might need to be revised upwards to suit operators' circumstances.
These estimates do not include the manpower required for repairs in case of findings.
A) Vacuum Loss inspection:
- Inspection: 1 man-hour per linear meter
- Hole restoration and resin curing time: 12 hours maximum elapsed B) ELCh inspection:
Note: Refer to Technical Disposition ref. TD/K4/S1/27583/2009 issue E for identification of inspection
- Location B: 4 man-hours
- Location C: 4 man-hours
- Location D: 1 man-hour
- Location E : 0.5 man-hours
- Location F : 3 man-hours Figures are given for one side shell to be inspected.
4.2 DESCRIPTION
4.2.1 JOB PREPARATION AND ACCESS Refer to Technical Disposition ref. TD/K4/S1/27583/2009 issue E paragraph "Job preparation"
4.2.2 INSPECTION INSTRUCTIONS Rudder shells must be inspected only in areas mentioned in Technical Disposition ref. TD/K4/S1/27583/2009 issue E Table 1.
Example: Rudder SN TS-2074 (end of table 1) This rudder must be inspected on L/H side shell, at trailing edge location only as per Technical Disposition location C.
as per Technical Disposition location C. It must be inspected on R/H side shell at trailing edge location only
4.2.2.1 FOR REINFORCED AREA Perform a one-time Vacuum Loss inspection according to Technical Disposition ref. TD/K4/S1/27583/2009 issue E location A.
Specific inspection instructions are to be requested by mail to:
Jean-Luc BOITEUX, SEES1 Customer Services Phone: +33 (0)5 61 93 18 69 Fax: +33 (0) 5 61 93 36 14 Mailto: jean-luc.j.boiteux@airbus.com
4.2.2.2 FOR TRAILING EDGE AREA perform three(3)-times repetitive ELCh inspection according to Technical Disposition ref. TD/K4/S1/27583/2009 issue E location B, C, CL, E and P.
~9719384.txt
4.2.2.3 FOR OTHER AREAS (LOWER RIB/UPPER EDGE/LEADING EDGE/OTHER
LOCATIONS) A. Pertorm a repetitive ELCh inspection according to Technical Disposition ref. TD/K4/S1/27583/2009 issue E locations D, F, G, H, J, K, L, M, N.
B.) Perform a one-time Vacuum Loss inspection according to specific Technical Dispositions. In order to obtain these instructions, please send a request to:
Jean-LuC BOITEUX, SEES1 Customer Services Phone: +33 (0) 5 61 93 18 69 Malito: jean-luc.j.boiteux@airbus.com 61 93 36 14 They will be provided in a time-frame compatible with the inspection planning (refer to paragraph 4.1).
4.2.3 JOB CLOSE UP Refer to Technical Disposition TD ref. TD/K4/S1/27583/2009 issue E paragraph "Job close up)".
4.2.4 ACTIONS IN CASE OF FINDINGS In case of findings, document accurately the relevant inspection report sheet, and contact Airbus at the following address before next flight to get further instructions:
SEER1/SEER2/SEER3 Customer Services Fax: +33 (0)5 61 93 28 73 regionl.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@airous.com
4.2.5 REPORTING If there are no findings, report to Airbus within 10 days from the inspection date of each affected rudder, at the following address:
Jean-Luc BOITEUX, SEES1 Customer Services Phone: +33 (0)5 61 93 18 69 Fax: +33 (0)5 61 93 36 14 Mailto: jean-luc.j.boiteux@airbus.com **BEG. REV**
4.2.6 MATERIAL, TOOLING Adjustable access platform or Cherry Picker Page 5
~9719384.txt
- Inspection equipment for ELCh as per REF.4
- Inspection equipment for Vacuum Loss inspection as per REF. 5
- Inspection equipment for Thermography as per REF. 6
- Inspection equipment for Tap test as per REF. 7
- Inspection equipment for Ultrasonic inspection as per REF. 8.
**END. REV** Note 1: In order for Airbus to provide adequate support to all affected operators, it is recommended to place a Purchase Order for ELCh tool two weeks ahead of the first scheduled inspection.
Note 2: A CD-Rom including ELCh familiarization has been shipped to all affected operators via Airbus Field Service stations.
**BEG.REV** Note 3: Instructions for restoration of Vacuum Loss inspection holes are detailed in the specific Technical Dispositions, and can be performed in 2 steps:
patches' by - Temporary restoration (option I): Hole closing with self-adhesive valid for 4500 FC. Correct cover application has to be frequent detailed visual inspections at intervals not exceeding 4 months/500 FH (whichever occurs first), until permanent reasona inspection in retioned areas fnd local thermography inspection in other areas must be performed before resin injection.
Final restoration has to be performed not later than 4500 FC.
End focal renogray inspection in Other areas use be peroned.
before resin injection.
**END. REV** Note 4: _For thermography inspection, as a limited number of equipment is available for loan from Airbus, necessary Infrared camera could also be purchased at the following address:
FLIR SYSTEMS Internet address: <http://www.flir.com/>
5. AOT APPROVAL The technical content of this AOT has been approved under the authority † EASA Design Organization Approval number EASA 21J.031.
t is anticipated that this AOT will be rendered mandatory.
6. REPORTING/ACKNOWLEDGMENT Operators are requested to acknowledge receipt of this AOT within 48 hours after receipt to:
R. LASCOURS, SEE E-mail: richard.lascours@airbus.com Fax number +33/ (0) 5.61.93.32.73 This acknowledgement can be made through the Airbus RCSM when available.
~9719384.txt Best regards, E. VAN AELST VICE PRESIDENT A300/A310/A300-600 PROGRAMME
CUSTOMER SERVICES DIRECTORATE If you receive this message via e-mail/internet, we draw your attention to the fact that it may be monitored and or intercepted.
Further, whilst Airbus has taken reasonable measures to ensure the integrity of this message and its contents, no warranty, whether express or implied, is given that the contents hereof conform to the original. In case of any doubt, please retrieve this document from your SITA address or Airbusworld system or request that it be retransmitted by fax or telex.