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CUSTOMER SERVICES DIRECTORATE 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE TELEPHONE + 33 (0)5 61 93 33 33
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A52L010-14 Page 1 of 5 Date: 30-SEP-2014 © AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
SUBJECT: ATA 52 – Inspection of forward cargo compartment door Beam3 area
AIRCRAFT TYPE: A330,A340,A340-500,A340-600, all models
OUR REF.: A52L010-14 dated 30-SEP-2014.
1. AIRCRAFT AFFECTED
This AOT is effective to all A330 and A340 aircraft up to MSN1416 included, equipped with the following FWD Cargo Door P/Ns (which are in pre MOD 50528 configuration). The listed P/Ns are affected, even handled as spares.
F523-70500-000 F523-70500-004 F523-70500-006 F523-70500-008 F523-70500-010 F523-70500-012 F523-70500-014 F523-70550-000 F523-70550-002 F523-70550-004 F523-70550-008 F523-70550-050
The following A/C have been equipped during production with above listed FWD Cargo Doors:
A340-200: MSN 4 to 178 A340-300: MSN 1 to 556 A330-200: MSN 181 to MSN 551 A330-300: MSN 12 to MSN 553 A340-600: MSN 360 to MSN 537 A340-500: MSN 394 to MSN 520
2. REFERENCED DOCUMENTATION
Ref.1: SRM 52-31-00 Fig.4 Sheet 2 Item 190/190A Ref.2: SRM 52-31-00 Fig.3 Sheet 1 Item 50/50A Ref.3: SRM 52-31-00 Fig.2 Sheet 1 Item 100 Ref.4: SRM 52-31-00 Fig.3 Sheet 1 Item 55/55A
Ref.5: AMM 52-31-15 PB.801 Ref.6: TFU 52.31.00.009
2.1 APPENDIX
Figure 1
ALERT OPERATORS TRANSMISSION - AOT
AOT ref: A52L010-14 Page 2 of 5 Date: 30-SEP-2014 © AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
3. REASON
3.1 FACTS
One operator reported recently two cases of crack findings on two different aircraft, at frame 20A Ref.1 and frame 20B Ref.2 close to beam 3 Ref.3. First finding was detected during scheduled maintenance.
The second finding was resulting from an inspection due to the first finding. At time of finding subject aircraft had accumulated 16,170 FC for the first case, and 16,556 FC for the second one.
The crack at frame 20A is visible from outside when the forward cargo door is open. The crack at frame 20B is hidden below the outer skin a nd the internal door lining. The failure scenario assumes that the first crack initiates at frame 20B leading to excessive loads at frame 20A and potential consequent cracking. Nevertheless, on one MSN a crack has been detected on frame 20A only.
3.2 CONSEQUENCES
Continued aircraft operation with rupture of both frames 20A & 20B will result in an overloading of the adjacent frame 21 Ref.4 also being hidden inside the door structure. Whilst full crack of the three frames has not yet been experienced in service so far, such scenario could lead to loss of structural integrity of the door. Moreover partial crack of frame 21 was never experienced.
3.3 AIM
The aim of this AOT is to request a one time inspection of frames 20A, 20B and 21 in the area of beam 3, until the half pitch between beam 2 and beam 3.
3.4 INVESTIGATION
Cracked frames have been recovered and will undergo a laboratory investigation.
4. SHORT TERM ACTION
4.1 PLANNING AND MANPOWER
4.1.1 ACCOMPLISHMENT TIMESCALE
For cargo doors, whose P/N’s are listed in para 1, perform a detailed visual inspection as described in para. 4.2 within 200 FC from AOT issuance date.
For spares cargo doors, whose P/N’s are listed in para 1, perform a detailed visual inspection as described in para. 4.2 prior to their installation on A/C.
4.1.2 MANPOWER
The estimated time to perform the inspection is 0.5 MH, access is 0.3 MH.
4.2 DESCRIPTION
4.2.1 ACCESS
Remove the forward portion of the internal door lining as per AMM Ref.5.
ALERT OPERATORS TRANSMISSION - AOT
AOT ref: A52L010-14 Page 3 of 5 Date: 30-SEP-2014 © AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
4.2.2 INSPECTION REQUIREMENTS
Perform a detailed visual inspection of frames 20A, 20B and 21 areas located above beam 3, from outside and inside with lining removed as follows:
FR20A, FR20B, FR21: Outer (attached) flange inner surface.
FR20A, FR20B, FR21: Web.
FR20A, FR20B, FR21: Inner (free) flange.
FR20A, FR20B, FR21: Door outer skin outer surface.
Refer to the figure 1 given as appendix.
4.2.3 FINDINGS
In case of crack finding the forward cargo door has to be repaired before next flight. Contact Airbus with a detailed damage assessment for further instructions. Depending on the finding, additional NDT inspection could be requested, a repair is needed in any case and part replacement could be necessary.
4.3 SPARES AND TOOLING
Spares parts have been speculated. For the materia l that may be needed, contact AIRBUS Spare department at hmv.spares@airbus.com or aog.spares@airbus.com
5. FURTHER INFORMATION
5.1 FOLLOW-UP PLAN
It is anticipated that this AOT will be rendered mandatory by issuance of an EASA Airworthiness Directive (AD).
Follow-up of this AOT will be done via TFU Ref.6.first issue targeted Q4 2014.
6. AOT APPROVAL
The technical content of this document is approved under the authority of DOA No. EASA.21J.031.
7. REPORTING
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:
Serge KIYMAZ Structure Engineer Structure Engineering – SEES1
CUSTOMER SERVICES Phone: +33(0)5 82 05 10 33 Fax: +33(0)5 61 93 36 14 Mailto: serge.kiymaz@airbus.com
ALERT OPERATORS TRANSMISSION - AOT
AOT ref: A52L010-14 Page 4 of 5 Date: 30-SEP-2014 © AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Best Regards,
Jean-Luc MOUYSSET
VICE PRESIDENT ENGINEERING SUPPORT
CUSTOMER SERVICES Philippe Gourdon VICE PRESIDENT A330/A340 PROGRAMME
CUSTOMER SERVICES
ALERT OPERATORS TRANSMISSION - AOT
AOT ref: A52L010-14 Page 5 of 5 Date: 30-SEP-2014 © AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
FIGURE 1
Fr20B Fr21 Fr20A Fr21 Fr20B Fr20A