EASA AD No.: 2014-0200R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0200R1

Date: 19 September 2014

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 EU 748/2012, Part 21.A.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 AD applies, except in accordance with the requirements of that AD, 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A310 aeroplanes

TCDS Number: EASA.A.172

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2014-0200 dated 08 September 2014, which superseded 

EASA AD 2008-0211 dated 08 December 2008.

ATA 57 Wings – Wing Top Skin Panels 1 and 2 at Rib 2 – Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A310 aeroplanes, all certified models, all manufacturer serial numbers.

Reason: Following scheduled maintenance, cracks were found around the wing top skin 

panels fastener holes at Rib 2, between Stringer (STG) 2 and STG14.

This condition, if not detected and corrected, could affect the structural integrity 

of the aeroplane. The General Visual Inspection required by the existing 

applicable Airworthiness Limitation Items (ALI) tasks may not be adequate to 

detect these cracks.

To address this issue, Airbus developed an inspection programme based on 

repetitive detailed inspections (DET) to ensure that any visible cracks in the wing 

top skin panels 1 and 2 along Rib 2 are detected in time and repaired 

appropriately. EASA issued AD 2008-0211 to require implementation of this 

inspection programme.

Since that AD was issued, Airbus improved the inspection programme with an

ultrasonic inspection to allow earlier crack detection, to subsequently reduce the 

scope of potential repair action, and to extend the intervals of the repetitive 

inspections.

For the reasons described above, this AD retains the requirements of EASA 

AD 2008-0211, which is superseded, and requires supplementary repetitive 

ultrasonic inspections of the wing top skin panel 1 and 2 between STG2 and

STG10 at Rib 2.

This AD is revised to correct an omission. Paragraph (2) addresses aeroplanes 

previously inspected, the numbering has changed for subsequent paragraphs.
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Effective Date: 22 September 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the initial compliance time and, thereafter, at intervals defined in 

Table 1 of this AD, as applicable to aeroplane model and Average Flight 

Time (AFT), accomplish the following actions concurrently and in sequence

in accordance with the instructions of Airbus Service Bulletin (SB)

A310-57-2096 Revision 02:

(1.1) Accomplish a DET around the fastener holes in the wing top skin 

panels 1 and 2, along Rib 2, between the front and rear spars on the 

left-hand (LH) and right-hand (RH) sides, and

(1.2) Accomplish an ultrasonic inspection around the fastener holes in the 

wing top skin panels 1 and 2, along Rib 2, between STG2 and 

STG10 on the LH and RH sides.

Table 1 – Inspection Threshold and Intervals,

whichever occurs first, flight hours (FH) or flight cycles (FC)

Aeroplane 

Models / AFT

Thresholds

(since aeroplane first flight)

Intervals

(not to exceed)

A310-200 37 400 FH

18 700 FC

4 100 FH

2 000 FC

A310-300 

(AFT < 4 hours)

48 400 FH

17 300 FC

5 600 FH

2 000 FC

A310-300 

(AFT ≥ 4 hours)

64 300 FH

12 800 FC

7 500 FH

1 500 FC

Note 1: For the purpose of this AD, the AFT should be established as follows for 

the determination of:

- The inspection threshold (TH), as the total accumulated FH, counted from 

take-off to touch-down, divided by the total accumulated FC at the effective 

date of this AD.

- The first inspection interval (INT), as the total accumulated FH divided by the 

total accumulated FC at the time of the TH inspection.

- The second inspection INT onwards, as the FH divided by the FC 

accumulated between the last two inspections.

(2) For aeroplanes already inspected before the effective date of this AD in 

accordance with the instructions of Airbus SB A310-57-2096 at original 

issue or Revision 01, the next inspection (DET and ultrasonic) after the 

effective date of this AD must be accomplished within the interval defined in 

Table 2 of this AD, as applicable. Subsequently, accomplish the actions as 

required by paragraph (1) of this AD.

(3) If no ultrasonic equipment is available for the first or the next due inspection 

as required by paragraph (1) of this AD, as applicable, accomplish the 

following actions:

(3.1) Accomplish a DET as required by paragraph (1.1) of this AD, as 

follows:

(3.1.1) For aeroplanes not inspected before the effective date of this 

AD: Within the initial compliance time defined in Table 1 of 

this AD.

(3.1.2) For aeroplanes already inspected before the effective date 

of this AD in accordance with the instructions of Airbus SB 

A310-57-2096 at original issue or Revision 01: Within the 

interval as defined in Table 2 of this AD.
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(3.2) Thereafter, without exceeding the intervals as defined in Table 2 of 

this AD, accomplish a DET and an ultrasonic inspection as required 

by paragraphs (1.1) and (1.2) of this AD.

(3.3) Subsequently, accomplish the actions as required by paragraph (1) 

of this AD.

Table 2 - Inspection Intervals for aeroplanes already inspected 

in accordance with Airbus SB A310-57-2096 at original issue 

or Revision 01

Aeroplane Models (AFT) Intervals (whichever occurs first,

FH or FC, since last inspection)

A310-200 3 500 FH

1 700 FC

A310-300 (AFT < 4 hours) 4 600 FH

1 600 FC

A310-300 (AFT ≥ 4 hours) 6 100 FH

1 200 FC

(4) If, during any inspection as required by paragraph (1) or (2) of this AD, as 

applicable, any cracks are found, before next flight, contact Airbus for 

approved repair instructions and accomplish those instructions accordingly.

Note 2: Repair of an aeroplane in accordance with approved Airbus instructions 

constitutes terminating action for the requirements of paragraph (1) of this AD 

only for the repaired area(s) of that aeroplane. Such areas must be inspected in 

accordance with the inspection programme defined in the Airbus repair 

instruction document.

Ref. Publications: Airbus SB A310-57-2096 original issue dated 06 May 2008, or Revision 01 

dated 05 August 2010, or Revision 02 dated 05 March 2014.

The use of later approved revisions of this document 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 original issue of this AD was posted on 30 July 2014 as PAD 14-128 for 

consultation until 27 August 2014. The Comment Response Document can 

be found at http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the Safety Information 

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 SAS – EIAW (Airworthiness Office)

E-mail: continued.airworthiness-wb.external@airbus.com.