CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

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AOT ref: A52L010-14 Page 1 of 5 Date: 30-SEP-2014

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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
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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 and 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.
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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 material 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
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Best Regards,

Jean-Luc MOUYSSET

VICE PRESIDENT ENGINEERING SUPPORT

CUSTOMER SERVICES

Philippe Gourdon

VICE PRESIDENT A330/A340 PROGRAMME

CUSTOMER SERVICES
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FIGURE 1

Fr21 Fr20B

Fr20A

Fr21 Fr20B Fr20A

INSPECTION TO BE PERFORMED 

FROM OUTSIDE AND INSIDE (LINING 

REMOVED) 

IN THE AREA ABOVE BEAM 3

BEAM 3

FORWARD