EASA AD No : 2009-0057 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0057 

Date: 13 March 2009 

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 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]. 

Type Approval Holder’s Name : 

AIRBUS SAS 

Type/Model designation(s) : 

A310 aeroplanes 

TCDS Number : France No 145 

Foreign AD : Not applicable 

Supersedure : None 

Note: This AD replaces the requirements of §§ 1.15 and 1.17 of EASA AD 2007-0053R1, which has 

been revised. 

ATA 57 Wings – Centre Wing Trellis Boom Drainage Holes & Frame 40 

Upper Corner Fitting – Inspection / Repair 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

A310-203, A310-203C, A310-204, A310-221, A310-222, A310-304, 

A310-308, A310-322, A310-324 and A310-325 aeroplanes, all serial 

numbers. 

Note: The detailed applicability for each of the actions required by this AD is 

identified in each relevant "Action" paragraph of the ‘Required Action(s) and 

Compliance Time(s)’ section of this AD. 

Reason: 

DGAC France AD 1992-106-132(B) original issue up to revision 7 was 

issued to require a set of inspection and modification tasks which addressed 

JAR/FAR 25-571 requirements related to damage-tolerance and fatigue 

evaluation of structure. 

Following the Extended Design Service Goal activities as part of the 

Structure Task Group for the Airbus A310 program, EASA published AD 

2007-0053, which replaced DGAC France AD F-1992-106-132R7. 

Since the issuance of AD 2007-0053R1, the thresholds and the intervals of 

Airbus Service Bulletins (SB) A310-57-2050 and A310-57-2064 have been 

updated. 

Consequently, this new AD takes over the requirements of paragraphs 1.15 

and 1.17 of EASA AD 2007-0053R1, which has been revised accordingly. 

In addition, and requires the accomplishment of Airbus SB A310-57-2048 at 

revision 01. 

Effective Date: 27 March 2009 
EASA AD No : 2009-0057 

EASA Form 110 Page 2/3 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Action No.1: Cold working of Trellis Boom Drainage Holes.

Applicable to A310-203, A310-203C, A310-204, A310-222, A310-304, 

A310-322 and A310-324 aeroplanes, all serial numbers, except those 

aeroplanes on which: 

- Airbus modification 06130 was embodied before delivery, or 

- Airbus SB A310-57-2048 has been embodied in service, or 

- any rework of cracked drain holes was previously performed in accordance 

with Airbus SB A310-57-2050 instructions, as applicable. 

(1) No later than the applicable thresholds defined in SB A310-57-2048 

revision 01, perform the cold working of trellis boom drainage holes in 

accordance with Airbus SB A310-57-2048 Revision 01. 

Action No.2: Inspection of Trellis Boom Drainage Holes.

Applicable to A310-203, A310-203C, A310-204, A310-221, A310-222, 

A310-304, A310-308, A310-322, A310-324 and A310-325 aeroplanes, all 

serial numbers . 

(2) No later than the applicable thresholds defined in SB A310-57-2050 

revision 01, perform the initial inspection of trellis boom drainage holes 

and, depending on findings, apply the corrective measures within the 

time period defined, in accordance with Airbus SB A310-57-2050 revision 

01. 

 Aeroplanes which have exceeded the values of the inspection thresholds 

must be inspected within the grace periods defined in SB A310-57-2050 

revision 01, taking the effective date of this directive as a starting date, 

and without exceeding the previous values quoted in the Airbus SB 

A310-57-2050 at original issue. 

Note 1: For aeroplanes previously inspected in accordance with Airbus SB 

A310-57-2050 at original issue, no further action is required by paragraph (2) 

of this AD. 

(3) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in Airbus SB A310-57-2050 revision 01 and, 

depending on findings, apply the corrective measures within the time 

period defined, in accordance with Airbus SB A310-57-2050 revision 01. 

 For the first planned repeat inspection to occur after the effective date of 

this directive, a grace period can be applied, without exceeding the 

interval value quoted in the Airbus SB A310-57-2050 original issue. 

Action No.3: Inspection of Fuselage Frame 40 Upper Corner Fitting.

Applicable to A310-203, A310-203C, A310-204, A310-221, A310-222, 

A310-304, A310-308, A310-322, A310-324 and A310-325 aeroplanes, all 

serial numbers. 

(4) No later than the applicable threshold defined in SB A310-57-2064 

revision 02, perform the initial inspection of the FR40 upper corner fitting 

LR & RH sides and, depending on findings, apply the corrective 

measures within the time period defined, in accordance with Airbus SB 

A310-57-2064 revision 02. 

 Aeroplanes which have exceeded the values of the inspection threshold 

must be inspected in the grace period defined in SB A310-57-2064 

revision 02, taking the effective date of this directive as a starting date, 

and without exceeding the previous values quoted in SB A310-57-2064 

at revision 01. 
EASA AD No : 2009-0057 

EASA Form 110 Page 3/3 

Note 2: For aeroplanes previously inspected in accordance with Airbus SB 

A310-57-2064 original issue or revision 01, no further action is required by 

paragraph (4) of this AD. 

(5) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in Airbus SB A310-57-2064 revision 02 and, 

depending on findings, apply the corrective measures within the time 

period defined, in accordance with Airbus SB A310-57-2064 revision 02. 

 For the first planned repeat inspection which occurs after the effective date 

of this directive, a delay (grace period) can be applied, without exceeding 

the interval value quoted in Airbus SB A310-57-2064 revision 01. 

(6) The accomplishment of corrective measures in accordance with Airbus SB 

A310-57-2050 and A310-57-2064 (at any revision) does not constitute 

terminating action for the repetitive inspection requirements of this AD. 

Ref. Publications: 

AIRBUS Service Bulletins : 

A310-57-2048 original issue or revision 01 

A310-57-2050 original issue or revision 01 

A310-57-2064 original issue, revision 01 or revision 02 

The use of a later approved revision 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. This AD was published on 13 January 2009 as PAD 09-013 for 

consultation until 03 February 2009. The Comment Response Document 

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

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 SAS – EAW (Airworthiness Office, 

Telephone:+ 33 5 61 93 36 96, Fax:+ 33 5 61 93 44 51)