EASA AD No.: 2014-0098-E

TE.CAP.00111-003 © 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 EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2014-0098-E

Date: 25 April 2014

Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean Community, its Member States and of the European third countries that participat e in the activities 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 HELICOPTERS Type/Model designation(s): AS 332 and EC 225 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage – Splice of Frame X5295 – Modification / I nspection / Repair

Manufacturer(s): Airbus Helicopters (formerly Euroc opter, Eurocopter France, Aerospatiale)

Applicability: AS 332 L2 helicopters, all serial nu mbers, if equipped with extended aluminium splices on frame X5295 installed in accordance with Airbus Helicopters modification (MOD) 0726517, or Service Bulletin (SB ) 53.01.52 or repair FR 332 53 507 06, and
EC 225 LP helicopters, all serial numbers, if equip ped with extended aluminium splices on frame X5295 installed in accordance with Airbus Helicopters MOD 0726517 or SB 53-003.

Reason: Prompted by several reports of cracks devel oped on helicopter frame X5295 EASA issued AD 2006-103R1 and AD 2007-0079 for AS33 2 helicopters, and AD 2006-0102R1 for EC225 helicopters to require rep etitive inspections of the affected frame. Those ADs also introduced an option al terminating action for the repetitive inspections, which consisted in rein forcement of the frame 5295 by installing aluminium splices on both right (RH) and left (LH) fuselage external skins of the helicopter in accordance with Airbus Helicopters MOD 0726517 or SB 53.01.52 or repair FR 332 53 507 06 o r SB 53-003 as applicable to helicopter model. Since those ADs wer e issued, during a scheduled inspection of an helicopter on which that terminating action had been embodied, a crack was detected on the modified fram e. The subsequent investigation revealed that the crac k initiated on one splice, in an area hidden by overlapping junction profile of t he cabin sliding door rail support, and then propagated to the frame. Optional Airbus Helicopters MODs are available (MOD 332A081354.00 or SB 05.00.84 for the AS332 helicopters, and MOD 0728090 or MOD 332A081354.00 or SB 05-019 f or the EC225EASA AD No.: 2014-0098-E

TE.CAP.00111-003 © 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. helicopters) installing a cut-out of affected rail support junction profile to allow a convenient access to identify cracks in an affected splice. Modification of a helicopter to embody the rail support cut-out allow s earlier detection of the crack initiation, therefore limits further damage a t frame X5295 level. However, the affected helicopter was not modified to embody that rail support junction profile cut-out.
This condition, if not detected and corrected, coul d lead to loss of structural integrity of the helicopter frame.
To address this potential unsafe condition, Airbus Helicopters issued Alert Service Bulletin (ASB) AS332-05.00.97 and ASB EC225 -05A038 to provide inspection instructions and, depending on findings, corrective action(s). These ASBs also provide installation instructions for a cut-out of junction profiles on the supports of both RH and left LH cabin sliding d oor rails.
For the reasons described above, this AD requires r epetitive inspections and, depending on the helicopter configuration, modifica tion of both RH and LH cabin sliding door rail supports.

Effective Date: 30 April 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Before next flight after the effective date of this AD, establish the helicopter configuration by reviewing helicopter delivery and/ or maintenance records to determine the following conditions:
(1.1) Determine if the helicopter is already modifi ed to embody the cutout the junction profiles of the supports of both, RH and left LH, cabin sliding door rails. Note 1: Cut-out of the cabin sliding door rail supp orts corresponds to Airbus Helicopters MOD 332A081354.00 or SB 05.00.84 for th e AS332 helicopters and Airbus Helicopters MOD 0728090 or MOD 332A081354.00 or SB 05-019, for the EC225 helicopters.
(1.2) Determine the flight hours (FH) accumulated b y the helicopter on the date when the aluminium splices on frame X5295 were installed.
Note 2: Installation of aluminium splices on frame X5295 corresponds to Airbus Helicopters MOD 0726517 for both AS332 and EC225 he licopters, or SB 53.01.52 or repair FR 332 53 507 06 or SB 53-003 as applicable to helicopter model.
(1.3) Determine the FH accumulated (on the effectiv e date of this AD) by the helicopter since installation of aluminium s plices on frame X5295 (see Note 2).
(2) If, during the review as required by paragraph (1) of this AD, it is determined that the helicopter was already modified in accordance with Airbus Helicopters SB 05.00.84 or SB 05-019, within 110 FH after the effective date of this AD, and, thereafter, at inte rvals not to exceed 110 FH, inspect both RH and LH aluminium splices on frame X 5295 in accordance with instructions of paragraph 3.B.3 of Airbus Heli copters ASB AS332- 05.00.97 or ASB EC225-05A038, as applicable to the helicopter model. (3) If, during the review as required by paragraph (1) of this AD, it is determined that the helicopter has not been modified in accordance with Airbus Helicopters SB 05.00.84 or SB 05-019, depend ing on configuration of the helicopter, within the compliance time(s) as specified in Table 1 of this AD, accomplish all the applicable actions.EASA AD No.: 2014-0098-E

TE.CAP.00111-003 © 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. Table 1: Compliance time and required actions depe nding on helicopter configuration

Aluminium splices on frame X5295 Required actions

Installed when the helicopter had accumulated equal to or more than 12 000 FH Within 50 FH after the effective date of this AD, comply with paragraph (3.1) of this AD,

or

Within 50 FH after the effective date of this AD, comply with paragraph (3.2) of this AD, and within 750 FH after the effective date of this AD, comply with paragraph (3.1) of this AD Installed before the helicopter had accumulated 12 000 FH, and the helicopter has accumulated at the effective date of this AD more than 1 650 FH since splices installation

Installed before the helicopter had accumulated 12 000 FH, and the helicopter has accumulated at the effective date of this AD less than or equal to 1 650 FH since splice installation. Before exceeding 1 700 FH accumulated since splice installation, comply with paragraph (3.1) of this AD

or Before exceeding 1 700 FH accumulated since installation of the splices, comply with paragraph (3.2) of this AD, and thereafter within 750 FH after the initial inspection as required by paragraph (3.2) of this AD comply with paragraph (3.1) of this AD

(3.1) Within the compliance time specified in Table 1 of this AD, as applicable, inspect and cut-out the junction profil es of the supports of both RH and left LH cabin sliding door rails, and, thereafter, at intervals not to exceed 110 FH, inspect both RH and LH aluminium splices on frame X5295 in accordance with instructi ons of Airbus Helicopters ASB AS332-05.00.97 or ASB EC225-05A038, as applicable to the helicopter model.
(3.2) Within the compliance time as specified in Ta ble 1 of this AD, as applicable, and, thereafter, at intervals not to ex ceed 50 FH, inspect the frame X5295 and the inner fuselage skins of fra me X5295 to detect cracks in accordance with the instructions o f Airbus Helicopters ASB AS332-05.00.97 or ASB EC225-05A038, as applicable to the helicopter model.
(3.3) Modification of a helicopter as required by p aragraph (3.1) of this AD constitutes terminating action for the repetitive i nspections specified in paragraph (3.2) of this AD.
(4) If, during modification of a helicopter as requ ired by paragraph (3.1) of this AD, any crack is found on one of the RH or LH splic es, before next flight, inspect the frame X5295 and the inner fuselage skin s of frame X5295 to detect cracks in accordance with instructions of Ai rbus Helicopters ASB AS332-05.00.97 or ASB EC225-05A038, as applicable t o the helicopter model. (5) If, during any inspection as required by paragr aph (2) or (3.1) of this AD, as applicable, any crack is found on one of the RH or LH splices, within 50 FH, repair the affected splice in accordance with a pproved AirbusEASA AD No.: 2014-0098-E

TE.CAP.00111-003 © 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. Helicopters repair instructions. (6) If, during any inspection as required by paragr aph (3.2) or (4) of this AD, as applicable, any crack is found on frame X5295, befo re next flight, repair the affected frame in accordance with approved Airbus H elicopters repair instructions. (7) If, during any inspection as required by paragr aph (3.2) or (4) of this AD, as applicable, any crack is found on inner fuselage sk ins of frame X5295 accomplish all the actions as required by paragraph s (7.1) and (7.2) of this AD. (7.1) After each Last-flight-of-the-day, inspect th e frame X5295 to detect cracks in accordance with the instructions of Airbu s Helicopters ASB AS332-05.00.97 or ASB EC225-05A038, as applicable t o the helicopter model. If during the inspection any crac k is found, before next flight, repair the affected frame in accordanc e with approved Airbus Helicopters repair instructions.
(7.2) Within 50 FH, repair the affected inner fusel age skins of frame X5295 in accordance with approved Airbus Helicopter s repair instructions. Concurrently with the repair, accompl ish a dyepenetrant inspection of frame X5295 to detect crack s and, if any crack is found, before next flight, repair the affe cted frame in accordance with approved Airbus Helicopters repair instructions.

Ref. Publications: Airbus Helicopters ASB AS332-05. 00.97 original issue, dated 15 April 2014. Airbus Helicopters ASB EC225-05A038 original issue, dated 15 April 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. The results of the safety assessment have indica ted the need for immediate publication and notification, without the full public consultation process. 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: Airbus Helicopters – Aéroport de Marseille Provence 13725 Marignane Cedex, France Telephone +33 (4) 42 85 97 97, Facsimile +33 (4) 42 85 99 66 E-mail: Directive.technical-support@eurocopter.com

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