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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-2016-9055; AD 2017-15-17 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
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CUSTOMER SERVICES DIRECTORATE AIRBUS 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE TELEPHONE + 33 (0)5 61 93 33 33
ALERT OPERATORS TRANSMISSION - AOT SUBJECT: ATA 57 - WINGS - CENTER WINGS - INSPECTION OF FRAME 40 LOWER OUTBOARD
RADIUS FOR CRACKS AIRCRAFT TYPE: A300-600 OUR REF.: A57W009-16 Rev 01 dated 13-JUL-2016.
0. REASON FOR REVISION The purpose of this revision is to extend the inspection area. Indeed, the adjacent fastener hole, not inspected as per revision 00, was found cracked while accomplishing this AOT.
The revised paragraphs are indicated between **BEG. REV** and **END REV**.
1. AIRCRAFT AFFECTED All A300-600 aircraft post MOD/MP 10221/S20394 (MSN 726 and subsequent)
2. REFERENCED DOCUMENTATION
2.1 APPENDIX **BEG. REV** Appendix 1: Extended inspection area **END REV** Appendix 2: Flowchart
2.2 REFERENCES SB 57-0261 rev00 AMM 24-00-00 AMM 32-12-11 AMM 06-41-57 AMM 57-41-41 NTM 51-10-08
3. REASON
3.1 FACTS A full stress analysis of the FR40 lower area, supported by a detailed Finite Element Model, of the configuration A300-600 post-mod 10221 was recently completed. This analysis demonstrated for the FR40 forward fitting lower radius:
- a low fatigue and propagation threshold a high probability to detect cracks on aircraft having accumulated more than 19000FC/41000FH In addition, on A300-B2 aircraft, which have a similar design, cracks were reported on the Full Scale Fatigue Test and on in-service aircraft. These aircraft are currently inspected through SB 57-0261 rev00.
Therefore, all A300-600 aircraft post MOD/MP 10221/S20394, close to or beyond 19000FC/41000FH, must be inspected in a short-time frame.
AOT ref: A57W009-16 Rev 01 Page 1 of 3 Date: 13-JUL-2016 © AIRBUS S.A.S. 2016. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
AIRBUS
ALERT OPERATORS TRANSMISSION - AOT
3.2 CONSEQUENCES A non-detected crack in this area could have an impact on the structural integrity of the FR40 forward fitting.
3.3 AIM The aim of this AOT is to call for a one-time High Frequency Eddy Current (HFEC) inspection of the FR40 forward fitting on A300-600 aircraft post MOD/MP 10221/S20394 (MSN 726 and subsequent).
4. SHORT TERM ACTION
4.1 PLANNING AND MANPOWER
4.1.1 ACCOMPLISHMENT TIMESCALE **BEG. REV** The one-time HFEC inspection described in paragraph 4.2.2 must be performed as follows:
- Not later than 19000FC/41000FH whichever occurs first (WOF), for aircraft with less or equal to 18700FC/40300FH at AOT issuance date,
- Within 300FC/630FH WOF from AOT issuance date, for aircraft with more than 18700FC/40300FH at AOT issuance date.
For aircraft already inspected as per revision 00 of this AOT, a one-time additional HFEC inspection, described in paragraph 4.2.2, must be performed within 300FC/630FH WOF from AOT revision 00 accomplishment date (see appendix 1 for extended inspection area).
**END REV**
4.1.2 MANPOWER The manpower estimates given in this AOT are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacturing and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included.
The estimated time for access is 2MH.
**BEG. REV** The estimated time to perform this extended inspection is 2MH **END REV** The estimated time for close-up is 2.5MH.
4.2 DESCRIPTION
4.2.1 ACCESS Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301.
Put access platforms in position at zones 510 and 610.
- Open main landing gear doors, refer to AMM 32-12-11, Page Block 301.
Open wing access doors 512AB, 512BB, 513AB, 612AB, 612BB, 613AB, refer to AMM 06-41-57, Page Block 001 and AMM 57-41-41, Page Block 401.
AOT ref: A57W009-16 Rev 01 Page 2 of 3 Date: 13-JUL-2016 © AIRBUS S.A.S. 2016. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
AIRBUS
ALERT OPERATORS TRANSMISSION - AOT
4.2.2 INSPECTION REQUIREMENTS Refer to appendix 2 for inspection instructions.
4.2.3 JOB CLOSE UP Make sure that the work areas are clean and clear of tools and other items of equipment.
Close wing access doors 512AB, 512BB, 513AB, 612AB, 612BB, 613AB, refer to AMM 06-41-57, Page Block 001 and AMM 57-41-41, Page Block 401.
Close main landing gear doors, refer to AMM 32-12-11, Page Block 301.
Remove the access platform(s).
Restore the systems and the aircraft to normal operating condition.
4.2.4 FINDINGS In case of findings, before next flight, please contact Airbus Customer Services Repair Teams SEOE1/SEOE2/SEOE3/SEOE4 through TechRequest on Airbus World, selecting Repair Domain to get further instructions.
4.3 SPARES AND TOOLING Not applicable
5. FURTHER INFORMATION
5.1 FOLLOW-UP PLAN **BEG. REV** This AOT will be cancelled and superseded by a new Inspection Service Bulletin, which will be available by Q1 2017.
**END REV**
5.2 IMPACTED DOCUMENTATION Not applicable
6. AOT APPROVAL The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.
It is anticipated that this AOT will be rendered mandatory.
7. REPORTING Questions about this AOT and inspection results with or without findings are to be addressed to Airbus Customer Services through TechRequest on Airbus World, selecting Engineering Domain and ATA
57-10.
Best Regards, Jean-Luc MOUY SSET Olivier CRIOU VICE PRESIDENT ENGINEERING SUPPORT HEAD OF A300/A310 PROGRAMME & CHIEF
CUSTOMER SERVICES ENGINEER
CUSTOMER SERVICES AOT ref: A57W009-16 Rev 01 Page 3 of 3 Date: 13-JUL-2016
• AIRBUS S.A.S. 2016. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Z140 FR47 RIB1 DATUM FR40
FRONT SPAR DATUM c
RH SHOWN
LH SYMMETRICAL AOT A57W009-16 Rev 01 - Appendix 1
AOT A57W009-16 Rev 01 - Appendix 1 Extended Inspection area
Do a HFEC inspection of the FR40 forward fitting outboard radius area As per NTM 51-10-08, LH/RH sides YES Crack? Contact Airbus before next flight NO No further action in the frame of this AOT AOT A57W009-16 Rev 01 - Appendix 2