EASA AD No.: 2014-0164

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0164

Date: 11 July 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 d ated 14 May 2014.



### ATA 53 Fuselage – Tail Cone / Trimmable Horizontal Stabili zer Support Struts at Frame 91 – Inspection / Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300, A300-600 and A310 aerop lanes, all certified models, all Manufacturer Serial Numbers (MSN) and Airbus A300F4-608ST aeroplanes, all MSN.

Reason: During scheduled maintenance, several Trimm able 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. Late ral 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 st rut. This condition, if not detected and corrected, 

### c ould lead to the rupture of all four THS support struts at FR91, which would make the re maining structure unable to carry limit loads, potentially resulting in loss of the Horizontal Tail Plane. To address this unsafe condition, EASA issued AD 20 14-0121 to require repetitive High Frequency Eddy Current (HFEC) inspe ctions of the THS support strut ends, installation of reinforcing clamps on s trut ends and, depending on findings, replacement of damaged support struts. In stallation of reinforcing clamps on strut ends is considered a temporary solu tion pending introduction of a re-designed support strut. Since that AD was issued, it was discovered that th e 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 wereEASA AD No.: 2014-0164

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. introduced through Airbus modification (mod) 06101, but may also have been installed in service as replacement parts on aeropl anes 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 n eed for an initial identification of the support struts installed on a eroplanes 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 previous ly: (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 instal led on the THS at FR 91 in accordance with the instructions of Airbus SB A3 00-53-0395, or SB A300-53-6174, or SB A310-53-2137, as applicable to aeroplane type/model. A check of the maintenance records is acceptable i n 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 re view. Note 1: No further action is required for aeroplane s 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 a re 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 a luminium support strut(s) P/N R21449 or P/N R21449D or P/N R21449G o r P/N R21449H, within the compliance time defined in Table 1 of th is AD, as applicable depending on aeroplane MSN and configuration, and, thereafter, at intervals not to exceed 24 months, accomplish a Hig h Frequency Eddy Current (HFEC) inspection of the THS aluminium supp ort 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 En ds

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 aerop lane 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. Co nfirm revision status through the EASA-Internet/Int ranet. (4) Concurrent with the initial inspection as requi red 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 clam ps previously installed and, before next flight after the inspect ion, install clamps on each strut end in accordance with the instructions of Ai rbus 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 parag raph (2) of this AD, any crack is found, before next flight, accomplish the applic able corrective action(s), depending on the inspection results, as specified i n 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 I nspection
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 cla mps 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 const itute terminating action for the repetitive inspections required by paragrap h (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 (incl uding 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 Feb ruary 2014. Airbus SB A300-53-6172 original issue, dated 14 Feb ruary 2014. Airbus SB A300-53-6174 original issue, dated 14 Feb ruary 2014. Airbus SB A300-53-9022 original issue, dated 05 Feb ruary 2014. Airbus SB A300-53-9024 original issue, dated 05 Feb ruary 2014. Airbus SB A310-53-2136 original issue, dated 14 Feb ruary 2014. Airbus SB A310-53-2137 original issue, dated 14 Feb ruary 2014. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA 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 Commen ts, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t 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. Co nfirm revision status through the EASA-Internet/Int ranet. AIRBUS SAS – EIAW (Airworthiness Office) E-mail: continued.airworthiness-wb.external@airbus.com.