CUSTOMER SERVICES DIRECTO RATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE
TELEPHONE + 33 (0)5 61 93 33 33



# ALERT OPERATORS TRANSMISSION

- AOT

AOT ref: A52L010

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- 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

- 0 06
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

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© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 3. REASON

3.1 FACTS

One operator reported recen tly 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 CONS EQUENCES

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 ser vice 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 thi s 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 issu ance 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 t o their installation on A/C

.

4.1.2 MANPOWER

T he 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.

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© 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: In ner (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

– S EES1
CUSTOMER SERVICES
Phone: +33 (0) 5 82 05 10 33 Fax: +33(0)5 61 93 36 14

Mailto: 

### serge.kiymaz@airbus.com

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© 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

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© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT



## FIGURE 1

Fr20B Fr2 1

F r20A

Fr2 1 Fr20B F r20A

INSPECTION TO BE PERFORMED

FROM OUTSIDE AND INSIDE (LINING REMOVED)

IN THE AREA ABOVE BEAM 3

BEAM 3 FORWARD