EASA AD No.: 2007-0053R3 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2007-0053R3 

Date: 17 December 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 

Revision : This AD revises and replaces EASA AD 2007-0053R2 dated 13 March 2009. 

ATA 53, 55, 57 Fuselage / Stabilisers / Wings – Structural Fatigue – Inspection / 

Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

A310 aeroplanes, all certified models, all manufacturer serial numbers (MSN). 

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

each relevant paragraph of the AD Compliance Section. The “Effectivity” 

paragraph of each SB that is referenced in this AD may be used by operators to 

determine which MSN is affected. 

Reason: 

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

issued in order to mandate a set of inspections/modifications which address 

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

evaluation of structure. 

Following the Extended Design Service Goal activities part of the Structure 

Task Group for the A310 program, EASA AD 2007-0053 superseded DGAC 

France AD F-1992-106-132R7 in order to take into account the publication of 

Airbus Service Bulletins (SB) A310-55-2004 at Revision 5 and Airbus SB 

A310-53-2074 at Revision 3, whose inspection thresholds and/or intervals had 

been reduced. 

Revision 1 of this AD was issued to remove the mandatory requirements related 

to the wings (i.e. § 1.8, 1.9, 1.10, 1.13, and 1.18) from the Compliance section, 

which have been transferred to EASA AD 2007-0242. 

Revision 2 of this AD has been issued to remove the mandatory requirements of 

paragraph 1.15, 1.16 and 1.17 which have now been transferred to EASA AD 
EASA AD No.: 2007-0053R3 

EASA Form 110 Page 2/4 

2009-0057 (§ 1.15 and 1.17) and 2009-0058 (§ 1.16) respectively. 

Revision 3 of this AD is issued to add a Note to the Applicability and amend the 

Required Action(s) and Compliance Time(s) section of this AD to clarify the 

allowed use of the referenced SBs by operators. In addition, a note has been 

added to paragraph 1.7 and the notes associated to paragraphs 1.1, 1.2, 1.3, 

1.4, 1.5 and 1.12 have been clarified. 

Effective Date: Revision 3: 01 January 2010 

Original issue, R1 and R2: 09 March 2007 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated: 

1. Unless already accomplished in accordance with any previous issues of 

DGAC France AD 1992-106-132(B), or with this AD at original release 

or revision 1 or revision 2, perform the initial inspections and/or 

modifications defined in the Airbus SB’s listed below. 

For paragraphs 1.2, 1.3, 1.4, 1.5, 1.6 and 1.12, comply with the 

instructions of below mentioned Service Bulletins at the defined 

thresholds or within 1 000 flight cycles (FC) following 17 June 1995 [the 

effective date of DGAC AD F-1992-106-132 Revision 3], whichever 

occurs later. 

For paragraph 1.1, comply with the instructions of below mentioned 

Service Bulletins at the defined thresholds or within 1 000 FC following 

15 June 1996 [effective date of AD F-1992-106-132 Revision 4], 

whichever occurs later. 

For paragraph 1.7, aeroplanes which have not been inspected in 

accordance with the requirements of AD F-1992-106-132 R7 must be 

inspected in accordance with the instructions of SB A310-55-2004 

Revision 5, at the defined thresholds or within 1 500 FC following the 

effective date of this AD, whichever occurs later. 

1.1. Airbus SB A310-53-2014 Revision 5 and Change Notice 5B: 

Fuselage - Centre Section - Reinforce bottom joint angle fitting at FR40. 

Note: paragraph 1.1 of this AD is not applicable to aeroplanes which 

received application of AIRBUS modification 04944 or 04800 before initial 

entry into service. 

1.2. Airbus SB A310-53-2016 Revision 5: 

Fuselage - Centre Section - FR47 and FR54 area - Provide local 

reinforcement. 

Note: paragraph 1.2 of this AD is not applicable to aeroplanes which 

received total application of AIRBUS modification 04980 before initial entry 

into service. 

1.3. Airbus SB A310-53-2054 Revision 2: 

Fuselage - Centre Section - Inspect frame reinforcement angle run out of 

FR46 between STGR21 and 22 LH/RH. 

Note: paragraph 1.3 of this AD is not applicable to aeroplanes which 

received application of AIRBUS modification 05254, or on which Airbus SB 

A310-53-2019R3 has been incorporated in service. 

Note: Carrying out the repair as detailed in Airbus SB A310-53-2054 

Revision 2 cancels the repetitive inspections requirements of paragraph 1.3 

of this AD. 

1.4. Airbus SB A310-53-2057 Revision 1: 

Fuselage - Centre Section - Inspection of the T-section connecting FR50A to 

the beam between FR50 and FR51 LH/RH. 

Note: paragraph 1.4 of this AD is applicable to aeroplanes which received 
EASA AD No.: 2007-0053R3 

EASA Form 110 Page 3/4 

application of AIRBUS modification 04853 except those aeroplanes which 

received application of AIRBUS modification 05273 or on which Airbus SB 

A310-53-2011 (any issue) has been incorporated in service. 

1.5. Airbus SB A310-53-2059 Revision 1: 

Fuselage - Inspect the lower side panel at the lap joint with the upper side 

panel at FR47 and STGR22, LH/RH. 

Note: paragraph 1.5 of this AD is not applicable to aeroplanes which 

received total application of AIRBUS modification 05997 before initial entry 

into service, or Airbus SB A310-53-2058 in service. 

Note: Carrying out a repair detailed in Airbus SB A310-53-2059 Revision 1 

cancels the repeat inspections requirements of paragraph 1.5 of this AD for 

the corresponding repaired area. 

1.6. Airbus SB A310-55-2002 Revision 4: 

Stabilizers - Horizontal Stabilizer Structure - Reinforcement of junction parts. 

Note: paragraph 1.6 of this AD is applicable to aeroplanes whose MSN is 

listed in Airbus SB A310-55-2002 Revision 4 

1.7. Airbus SB A310-55-2004 Revision 5: 

Stabilizer - Horizontal Tailplane Structure - Inspection program after 

reinforcement as per mod. 04933 in production or by the embodiment of 

Airbus SB A310-55-2002 in service. 

Note: paragraph 1.7 of this AD is not applicable to aeroplanes which 

received application of AIRBUS modification 06070 before initial entry into 

service.

1.8. Transferred to EASA AD 2007-0242. 

1.9. Transferred to EASA AD 2007-0242. 

1.10. Transferred to EASA AD 2007-0242. 

1.11. Cancelled by Revision 6 of DGAC AD F-1992-106-132 

1.12. Airbus SB A310-57-2039 Original Issue: 

Wings - Centre wing - Inspection of front spar web vertical posts. 

Note: paragraph 1.12 of this AD is not applicable to aeroplanes which 

received application of AIRBUS modification 04977 before initial entry into 

service. 

1.13. Transferred to EASA AD 2007-0242.

1.14. Cancelled by Revision 7 of DGAC AD F-1992-106-132 

1.15. Transferred to EASA AD 2009-0057. 

1.16. Transferred to EASA AD 2009-0058. 

1.17. Transferred to EASA AD 2009-0057. 

1.18. Transferred to EASA AD 2007-0242. 

2. Repeat the inspections defined in the SB’s mentioned in paragraph 1 

above, in accordance with the intervals indicated in each of the SB’s 

when applicable. 

After 09 March 2007 (the effective date of the original issue, R1 and R2 

of this AD), for paragraph 1.7, accomplish the instructions of Airbus SB 

A310-55-2004 Revision 5 at the intervals defined therein, following the 

latest inspection or within the grace period defined in Airbus SB A310-

55-2004 Revision 5, whichever occurs later and without exceeding the 

previous requirements as defined in DGAC France AD F-1992-106-
EASA AD No.: 2007-0053R3 

EASA Form 110 Page 4/4 

132R7. 

Note: Operators may also determine, by referring to the appropriate SB, 

under which condition(s) the relevant inspection program may be 

terminated. 

Ref. Publications: 

AIRBUS Service Bulletins: 

A310-53-2014 Revision 5 and change notice 5B 

A310-53-2016 Revision 5 

A310-53-2054 Revision 2 

A310-53-2057 Revision 1 

A310-53-2059 Revision 1 

A310-55-2002 Revision 4 

A310-55-2004 Revision 3, Revision 4 or Revision 5 

A310-57-2039 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 original issue of this AD was posted on 21 November 2006 as 

PAD 06-251 for consultation until 21 December 2006 and republished on 

14 December 2006 as PAD 06-251R1, for consultation until 04 January 

2007. 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)