EASA AD No.: 2011-0007R1 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0007R1 

Date: 14 February 2011 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States 

and of the European third countries that participate in the activities of EASA under Article 

66 of that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, 

the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person 

may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that 

Airworthiness Directive unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the 

Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

AIRBUS

Type/Model designation(s) : 

A330 and A340 aeroplanes 

TCDS Number : EASA.A.004 and EASA.A.015 

Foreign AD : Not applicable 

Revision : This AD revises EASA AD 2011-0007 dated 18 January 2011 

ATA 52 Doors – Forward and Aft Cargo Compartment Doors – 

Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -223F, -243, -

243F, -301, -302, -303, -321, -322, -323, -341, -342 and -343, all 

manufacturer serial numbers. 

Airbus A340 aeroplanes, models -211, -212, -213, -311, -312 and -313, all 

manufacturer serial numbers. 

Reason: Two operators have reported cases of some sheared fasteners on the 

outside skin of the forward cargo door, detected during walk around 

checks. Further inspections revealed crack findings on the frame (FR) fork 

ends. 

In addition, during a scheduled maintenance check, the aft cargo door 

frame 64A of an aeroplane has been found cracked for a length of more 

than 3 inches. Outer skin rivets were also found sheared. At time of 

findings the aeroplane had accumulated 10564 flight cycles (FC), i.e. 

below the 12000 FC threshold defined in DGAC France AD F-2001-124(B) 

and DGAC France AD F-2001-126(B), which require a special detailed 

inspection of the aft cargo compartment door. 

In case of cracked or ruptured (forward or aft) cargo door frame, the loads 

will be transferred to the remaining structural elements. Such second load 

path is able to sustain the loads for a limited number of flight cycles only. 

Rupture of two vertical frames could result in the loss of the structural 

integrity of the forward or aft cargo door. 
EASA AD No.: 2011-0007R1 

EASA Form 110 Page 2/3 

For the above described reasons, this AD requires repetitive detailed 

visual inspections of the aft and forward cargo doors outer skin for 

sheared, loose or missing rivets at all frame fork ends and the 

accomplishment of the applicable corrective actions. 

This AD is considered to be an interim action, further actions might be 

required to revise/supersede the above mentioned DGAC France ADs. 

This AD is revised in order to recognize that aeroplanes on which Airbus 

modification 44852 has been embodied in production are not affected by 

the repetitive inspection requirements of this AD on the Aft Cargo 

Compartment Door. 

Effective Date: Revision 01 : 28 February 2011 

Original issue : 01 February 2011 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Forward Cargo Compartment Door

(1) Before the accumulation of 6 000 total FC since the aeroplane first 

flight or within 400 FC after the effective date of this AD at original 

issue, whichever occurs later, perform a detailed visual inspection of 

outer skin rivets at the frame fork ends between FR20B and FR25 of 

the forward cargo door, in accordance with the instructions of All 

Operators Telex (AOT) A330-52A3085 or AOT A340-52A4092, as 

applicable to aeroplane type. 

(2) Repeat the inspection defined in paragraph (1) of this AD at intervals 

not to exceed 800 FC from the last inspection. 

Aft Cargo Compartment Door 

(3) For All A330 and A340 aeroplanes identified in the applicability section 

of this AD except those on which Airbus modification (mod.) 44854 or 

mod. 44852 has been embodied in production or Airbus Service 

Bulletin (SB) A330-52-3044 or SB A340-52-4054 has been embodied 

in service:

(3.1) Before the accumulation of 4 000 total FC since the aeroplane first 

flight or within 400 FC after the effective date of this AD at original 

issue, whichever occurs later, perform a detailed visual inspection 

of outer skin rivets at the frame fork ends between FR60 and 

FR64A of the Aft cargo door, in accordance with the instructions of 

AOT A330-52A3084 or AOT A340-52A4091, as applicable to 

aeroplane type. 

(3.2) Repeat the inspection defined in paragraph (3.1) of this AD at 

intervals not to exceed 400 FC from the last inspection. 

(4) If any discrepancy is found during the initial or repetitive inspections 

required by paragraph (1) or (2) or (3.1) or (3.2) of this AD, before 

further flight, contact Airbus to obtain the necessary approved 

instructions for corrective action and accomplish those instructions 

accordingly. 

Ref. Publications: All Operators Telex A330-52A3084 dated 20 December 2010 

All Operators Telex A330-52A3085 dated 20 December 2010 

All Operators Telex A340-52A4091 dated 20 December 2010 

All Operators Telex A340-52A4092 dated 20 December 2010 
EASA AD No.: 2011-0007R1 

EASA Form 110 Page 3/3 

Airbus Service Bulletin A330-52-3044 at Original Issue 

Airbus Service Bulletin A340-52-4054 at Original Issue. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements 

in this AD, please contact: 

AIRBUS – Airworthiness Office – EAL; 

E-mail: airworthiness.A330-A340@airbus.com.