EASA AD No.: 2014-0164

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/4 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0164 

Date: 11 July 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): 

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

aeroplanes 

TCDS Numbers: EASA.A.014 and EASA.A.172 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA AD 2014-0121 dated 14 May 2014. 

ATA 53 Fuselage – Tail Cone / Trimmable Horizontal Stabilizer Support 

Struts at Frame 91 – Inspection / Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300, A300-600 and A310 aeroplanes, all certified models, all 

Manufacturer Serial Numbers (MSN) and 

Airbus A300F4-608ST aeroplanes, all MSN. 

Reason: During scheduled maintenance, several Trimmable Horizontal Stabilizer (THS) 

support struts were found cracked at the strut ends. The THS is supported and 

articulated at frame (FR) 91 in the tail cone. Lateral movement is prevented by 

four diagonal support struts. 

Investigations revealed that the cracks were caused by stress corrosion and 

propagated from the inside to the outside of the strut. 

This condition, if not detected and corrected, could lead to the rupture of all four 

THS support struts at FR91, which would make the remaining structure unable 

to carry limit loads, potentially resulting in loss of the Horizontal Tail Plane. 

To address this unsafe condition, EASA issued AD 2014-0121 to require 

repetitive High Frequency Eddy Current (HFEC) inspections of the THS support 

strut ends, installation of reinforcing clamps on strut ends and, depending on 

findings, replacement of damaged support struts. Installation of reinforcing 

clamps on strut ends is considered a temporary solution pending introduction of 

a re-designed support strut. 

Since that AD was issued, it was discovered that the AD appeared to also 

require HFEC inspections of steel struts, which are not prone to cracking. The 

unsafe condition exists only on support struts made of aluminium, which were 
EASA AD No.: 2014-0164

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/4 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

introduced through Airbus modification (mod) 06101, but may also have been 

installed in service as replacement parts on aeroplanes in pre-mod 06101 

configuration. 

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

2014-0121, which is superseded, and clarifies the need for an initial 

identification of the support struts installed on aeroplanes in pre-mod 06101 

configuration. The related Airbus Service Bulletins (SB) remain unchanged. 

Effective Date: 25 July 2014 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) For aeroplanes in pre-mod 06101 configuration, within 12 months after 28 

May 2014 [the effective date of EASA AD 2014-0121], inspect and identify 

the part numbers (P/N) of each support strut installed on the THS at FR 91 

in accordance with the instructions of Airbus SB A300-53-0395, or SB 

A300-53-6174, or SB A310-53-2137, as applicable to aeroplane 

type/model. 

 A check of the maintenance records is acceptable in lieu of the inspection, 

provided those records can be relied upon for that purpose and the support 

strut P/N can be positively identified from that review. 

Note 1: No further action is required for aeroplanes in pre- mod 06101 

configuration, unless one or more aluminium support strut(s) P/N R21449 or 

P/N R21449D or P/N R21449G or P/N R21449H have been found installed. 

Note 2: Aeroplanes in pre-mod 06101 configuration are known to range from 

MSN 0001 through MSN 0498 inclusive. 

(2) For aeroplanes in post mod 06101 configuration, and aeroplanes in premod 06101 configuration equipped with one or more aluminium support 

strut(s) P/N R21449 or P/N R21449D or P/N R21449G or P/N R21449H, 

within the compliance time defined in Table 1 of this AD, as applicable 

depending on aeroplane MSN and configuration, and, thereafter, at 

intervals not to exceed 24 months, accomplish a High Frequency Eddy 

Current (HFEC) inspection of the THS aluminium support strut ends at 

FR91 in accordance with the instructions of Airbus SB A300-53-0395, or 

SB A300-53-6174, or SB A300-53-9024, or SB A310-53-2137, as 

applicable to aeroplane type/model: 

Table 1: Initial Inspection of THS Support Strut Ends 

MSN / Configuration 

Compliance Time 

(after 28 May 2014, the effective 

date of EASA AD 2014-0121) 

MSN 0499 through MSN 0747 

inclusive (post mod 06101) 

Within 12 months 

MSN 0748 through MSN 0878 

inclusive (post mod 06101) 

Within 18 months 

MSN 0001 through MSN 0498 

inclusive (pre-mod 06101), if 

one or more aluminium strut(s) 

have been identified. 

Within 24 months 

(3) Reinforcing clamps installed on strut ends must be removed before 

accomplishment of each HFEC inspection as required by paragraph (2) of 

this AD, and re-installed after the inspection, in accordance with the 

instructions of Airbus SB A300-53-0395, or SB A300-53-6174, or SB A300-

53-9024, or SB A310-53-2137, as applicable to aeroplane type/model. 
EASA AD No.: 2014-0164

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/4 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

(4) Concurrent with the initial inspection as required by paragraph (2) of this 

AD, identify aluminium support strut(s) P/N R21449 or P/N R21449D or 

P/N R21449G or P/N R21449H with no reinforcing clamps previously 

installed and, before next flight after the inspection, install clamps on each 

strut end in accordance with the instructions of Airbus SB A300-53-0394, or 

SB A300-53-6172, or SB A300-53-9022, or SB A310-53-2136, as 

applicable to aeroplane type/model. 

(5) If, during any inspection as required by paragraph (2) of this AD, any crack 

is found, before next flight, accomplish the applicable corrective action(s), 

depending on the inspection results, as specified in Table 2 of this AD, in 

accordance with the instructions of Airbus SB A300-53-0395, or SB A300-

53-6174, or SB A300-53-9024, or SB A310-53-2137, as applicable to 

aeroplane type/model. 

Table 2: Corrective Action(s) after THS Strut End Inspection 

Inspection Result Corrective Action(s) 

A crack of more than 15 mm or 

more than four cracks of 15 mm 

or less were found on one strut 

end 

Replace the affected THS support 

strut with a serviceable part and 

install clamps on each strut end 

No more than four cracks of 

15 mm or less were found on a 

strut end 

Install clamps on each strut end 

(6) Installation on an aeroplane of reinforcing clamps as required by paragraph 

(4) of this AD or replacement of support struts and/or clamp installation as 

required by paragraph (5) of this AD does not constitute terminating action 

for the repetitive inspections required by paragraph (2) of this AD for that 

aeroplane. 

(7) Within 30 days after the initial inspection as required by paragraph (2) of 

this AD, report the results of the inspection (including no findings) to Airbus. 

Ref. Publications: Airbus SB A300-53-0394 original issue, dated 14 February 2014. 

Airbus SB A300-53-0395 original issue, dated 14 February 2014. 

Airbus SB A300-53-6172 original issue, dated 14 February 2014. 

Airbus SB A300-53-6174 original issue, dated 14 February 2014. 

Airbus SB A300-53-9022 original issue, dated 05 February 2014. 

Airbus SB A300-53-9024 original issue, dated 05 February 2014. 

Airbus SB A310-53-2136 original issue, dated 14 February 2014. 

Airbus SB A310-53-2137 original issue, dated 14 February 2014. 

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication. 

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

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

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

this AD, please contact: 
EASA AD No.: 2014-0164

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 4/4 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

AIRBUS SAS – EIAW (Airworthiness Office) 

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