On this page
ADs that cite it · 1
Newest first, with the revision each names, as OpenAirDocs read it from the AD’s text: check it against the AD.
Text · 8OCR
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-2010-1309; AD 2011-08-12 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = 'fb556bd859d3f8bcaf2ccee282365e2ecb4a1f6cecc52a92ccf06b7dc6f51492' ORDER BY p.page"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = 'fb556bd859d3f8bcaf2ccee282365e2ecb4a1f6cecc52a92ccf06b7dc6f51492' ORDER BY p.page
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
ALL OPERATORS TELEX - ALL OPERATORS TELEX SUBJECT: A340- ATA 55-40 - INSPECTION OF RUDDER SIDE SHELLS FOR
POTENTIAL SKIN TO HONEYCOMB DISBOND OUR REF: AOT A340-55A4036 Rev 02 dated 30 September 2009 OUR PREVIOUS REF: AOT A340-55A4036 Rev 01 dated 08 July 09 AOT A330-55A4036 Rev 00 dated 27 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 as required by AOT A340-55A4036 Rev.01 and as defined in the specific Technical Dispositions for reinforced areas location A. The thermography inspection requirements remain applicable in nonreinforced areas as defined in the specific Technical Dispositions for location D.
- Introduce minor changes in Technical Disposition TD/K4/S3/27733/2009, now revised at issue E:
- 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 have been included in appendix A.
- Airline/MSN cross-references have been updated where necessary.
- 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 A340-55A4036 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 21 months from restoration date is required.
The revised paragraphs are indicated between **BEG.REV** and **END.REV**.
1. AIRCRAFT AFFECTED All A340-200/300 aircraft equipped with rudders having the Serial 1
Numbers (SN) listed in Technical Disposition ref. TD/K4/S3/27733/2009 issue E Table 1, and having accumulated 13000 FC or more since their first installation on aircraft at receipt date of this AOT at original issue.
Note: Affected rudders listed in Technical Disposition ref.
TD/K4/S3/27733/2009 issue E Table 1, and having accumulated less than 13000 FC at receipt date of this AOT at original issue are also to be inspected according to the AOT's instructions. However for these rudders the accomplishment timescale given in paragraph 4.1.1 has to be considered from the date when the 13000 FC threshold is reached.
In case a rudder originally fitted on one aircraft (refer to Aircraft Inspection Report delivery document) has been removed and installed on another aircraft, it is the 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 in TD/K4/S3/27733/2009 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: A340 SRM 55-41-13 Fig. 1 item 1/20, 5/25, 10/30 depending on mod REF.3: Technical Disposition ref. TD/K4/S3/27733/2009 issue E REF.4. NTM TASK 51-10-26-220-801 (ELCh inspection) REF 5: NTM TASK 51-10-28-220-801 (Vacuum Loss inspection) REF 6: NTM TASK 55-40-02-290-801 (Thermography inspection) REF 7: NTM TASK 51-10-19-280-801 (Tap test inspection) REF 8: NIM TASK 51-10-24-270-801 NTM Temporary Revision TR 51-003 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 2
occurred as a consequence of excessive temperature applied, during a hot curing rework of the inner skin in production. This rework occurred outside autoclave.
Such hot curing reworks were also performed on some A340 rudders.
Operators were informed thru OIT REF.1 dispatched in November 2008 and revised in March 2009.
3.2 AIM 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:
Wera 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/S3/27733/2009 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 1800 FH from the receipt date of this AOT at original issue.
**BEG.REV**
4.1.1.2 FOR TRAILING EDGE AREA
The ELCh inspection described in paragraph 4.2.2.2 must be performed within 21 months from the receipt date of this AOT at original issue, and repeated twice at intervals not exceeding 4500 FC, but no less than 4000 FC since last inspection.
Following 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 1800 FH from the receipt date of this AOT at original issue
- then, repeated at intervals not exceeding 1800 FH
- up to accomplishment of the terminating one-time Vacuum Loss inspection mentioned in paragraph 4.2.2.3.B., that must be performed within 21 months from the receipt date of this AOT at original issue.
Accomplishment of this terminating one-time inspection cancels the repetitive ELCh inspection requirements described in paragraph If the vacuum loss inspection is performed within 1800 FH from the receipt date of the AOT at original issue, 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 time B) ELCh inspection:
Note: Refer to Technical Disposition ref. TD/K4/S3/27733/2009 issue E for identification of inspection areas:
- Location B: 4 man-hours
- Location C: 4 man-hours
- Location D: 1 man-hour
- Location E: 0.5 man-hour 4
4.2 DESCRIPTION
4.2.1 JOB PREPARATION AND ACCESS Refer to Technical Disposition ref. TD/K4/S3/27733/2009 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/S3/27733/2009 issue E Table 1.
Example: Rudder SN TS-2018 (end of table 1) This rudder must be inspected on L/I side, at lower rib location only as per Technical Disposition location D.
No inspection is required on R/H side shell.
4.2.2.1 FOR REINFORCED AREA Perform a one-time Vacuum Loss inspection according to Technical Disposition ref. TD/K4/S3/27733/2009 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/S3/27733/2009 issue E locations B, B2, C and E.
4.2.2.3 FOR OTHER AREAS (LOWER RIB/UPPER EDGE/LEADING
EDGE/OTHER
LOCATIONS) A.) Perform a repetitive ELCh inspection according to Technical Disposition ref. TD/K4/S3/27733/2009 issue E location D.
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 Fax: +33 (0)5 61 93 36 14 5
Mailto: jean-luc.j.boiteux@airbus.com 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/S3/27733/2009 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 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
4.2.5 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
- Inspection equipment for ELCh as per REF.4 6
- 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:
Temporary restoration (option I): Hole closing with selfadhesive patches, valid for 21 months. Correct cover application has to be ensured by frequent detailed visual inspections at an interval not exceeding 900 FH, until permanent restoration is performed, or Temporary restoration (option II): Hole filling with resin.
Local ultrasonic inspection in reinforced areas and local thermography inspection in other areas must be performed before resin injection.
Final restoration has to be performed no later than 21 months after temporary restoration.
Permanent restoration: Hole filling with resin and restoration of surface protection. Local ultrasonic inspection in reinforced areas and local thermography inspection in other areas must be performed 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 of EASA Design Organization Approval number EASA 21J.031.
It 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:
MR. 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.
Best regards, J. GROTHER VICE PRESIDENT A330/A340 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 or request that it be retransmitted by fax