EASA AD No.: 2008-0052R1 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2008-0052R1 

Date: 30 June 2008 

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) : 

A300, A310, A300-600 and A300-600ST aircraft 

TCDS Numbers : France No 145 and EASA A.014 

Foreign AD : Not applicable 

Revision : This AD revises and replaces EASA AD 2008-0052 dated 05 March 2008, 

including the Corrections thereof, dated 10 March 2008 and 12 March 2008. 

ATA 32 Landing Gear – Nose Landing Gear Shock Absorber/Barrel 

Attachment Bolts – Inspection / Re-Torque / Replacement 

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE) 

Applicability: 

AIRBUS A300, A310 and A300-600 aircraft, all certified models, all serial 

numbers, except those aircraft on which AIRBUS modification No. 13212 has 

been embodied in production or AIRBUS Service Bulletin (SB) A300-32-0453 or 

A310-32-2135 or A300-32-6099 has been embodied in service; and 

AIRBUS A300F4-608ST aircraft, all serial numbers, except those aircraft on 

which SB A300-32-9016 has been embodied in service (AIRBUS modification 

No. 19604). 

Reason: 

Two cases of complete nose landing gear (NLG) shock absorber bolts failure 

were reported to the manufacturer. In both cases, the crew was unable to 

retract the gear and was forced to an In Flight Turn Back. In one case, the 

aircraft experienced a low speed runway excursion. The root cause of the 

bolts failure has been identified being due to a bolt(s) over-torque. The 

investigation has highlighted that the design of the NLG shock absorber was 

not tolerant to the over-torque and an inspection plan has been developed to 

track any NLG shock absorber-to-main barrel attachment bolts status. The 

preliminary inspection plan, required by DGAC France Airworthiness Directive 

(AD) F-2004-075 and F-2004-076, has allowed limiting the number of 

findings: high at the initial inspection, it has decreased following the repetitive 

inspections. 

This new AD retains the requirements of those ADs, which are superseded, 

and requires a repetitive torque check of the NLG shock absorber-to-main 

barrel attachment bolts with new thresholds and intervals. This new AD also 

refers to an optional modification as terminating action. 
EASA AD No.: 2008-0052R1 

EASA Form 110 Page 2/3 

AD 2008-0052 has been revised to take into account the various corrective 

measures resulting in specific inspection intervals and paragraph (1) of the 

Compliance section has been amended accordingly. In addition, paragraph 

(3) has been changed to correct the compliance time allowed for aircraft that 

have already exceeded the threshold for the initial torque check. 

Effective Date: 19 March 2008 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 30 days or 1 000 Flight Cycles (FC), whichever occurs later after 

26 May 2004 [the effective date of AD F-2004-075 and F-2004-076] 

depending on previous NLG overhaul or previous attachments bolts 

replacement, and thereafter at intervals depending on inspection results 

and the corrective measures undertaken, inspect the NLG shock 

absorber-to-main barrel attachment bolts and take corrective actions in 

accordance with the instructions of and within the associated time 

period(s) as defined in Airbus All Operator Telex (AOT) A300-32A0447 or 

A310-32A2132 or A300-32A6093 or A300-32A9009. 

(2) After the effective date of this directive, at the later of the thresholds 

specified below: 

- Within 3 200 FC or 30 months since NLG first flight, whichever occurs 

first; or 

- Within 3 200 FC or 30 months accumulated by the NLG since 

installation of new bolts, whichever occurs first, 

 and thereafter at intervals not to exceed 3 200 FC or 30 months time-inservice accumulated by the NLG, whichever occurs first, do a check of 

the torque load of the nuts of the NLG shock absorber to main barrel 

attachment bolts and depending of the torque load value: 

- retighten the bolt(s) or replace the bolt(s); or 

- replace all bolts, 

 in accordance with the instructions of SB A300-32-0447 revision 1 or 

A310-32-2132 revision 1 or A300-32-6093 revision 1 or A300-32-9009 

revision 1, as applicable. 

(3) If, on the effective date of this AD, one of the thresholds of paragraph (2) 

has already been exceeded, perform the initial actions as required by 

paragraph (2) within 3 200 FC or 30 months, whichever occurs first after 

the effective date of this AD. 

Note 1: After accomplishment of the initial inspection in accordance with 

paragraph (2) or paragraph (3) of this AD, as applicable, the repetitive 

inspections of paragraph (1) are no longer required. 

Note 2: For aircraft on which AIRBUS Service Bulletin (SB) A300-32-0453 or 

A310-32-2135 or A300-32-6099 or A300-32-9016 has been installed, the 

requirements of this AD are no longer applicable. 

(4) Within 30 days after each inspection that results in re-torque or 

replacement of bolt(s), send a report to AIRBUS, using Appendix 01 of 

SB A300-32-0447 revision 1 or A310-32-2132 revision 1 or A300-32-6093 

revision 1 or A300-32-9009 revision 1, as applicable. 

Ref. Publications: 

AIRBUS AOT A300-32A0447 original issue; A310-32A2132 original issue; 

A300-32A6093 original issue; A300-32A9009 original issue; 

AIRBUS Inspection Service Bulletin A300-32-0447 revision 1; A310-32-2132 

revision 1; A300-32-6093 revision 1; A300-32-9009 revision 1. 

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

compliance with the requirements of this AD. 
EASA AD No.: 2008-0052R1 

EASA Form 110 Page 3/3 

Remarks :

1. If requested and appropriately substantiated, EASA can accept Alternative 

Methods of Compliance for this AD. 

2. This AD was first posted on 08 October 2007 as PAD 07-171 for 

consultation until 05 November 2007. The Comment Response Document 

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

3. Enquiries regarding this AD should be referred to the AD Focal Point - 

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.