Prescrizione di Aeronavigabilità

Rif. N.
2012-268 del
03/ago/12
Prescrizione di Aeronavigabilità
Airworthiness Directive
Si allega la Prescrizione di Aeronavigabilità emessa dalla:
Attached the Airworthiness Directive issued by:
Agenzia Europea per la Sicurezza Aerea
European Aviation Safety Agency
Autorità Primaria di Certificazione
Primary Certification Authority
RIFERIMENTO AD
AD Reference
EASA N. 2012-0139
COSTRUTTORE
Manufacturer
AgustaWestland S.p.A.
SOGGETTO
Applicability
A119 helicopters
OGGETTO
Subject
Landing Gear – Skid Landing Gear Forward Crossbeam Assembly –
Inspection / Replacement
NOTE
Remark
Nota 1
Il Certificato di Navigabilità dell'aeromobile sulle cui strutture od impianti deve essere applicata la Prescrizione
di Aeronavigabilità a riferimento, scade di validità qualora essa non venga attuata nei termini prefissati.
The Certificate of Airworthiness of the aircraft to which structures and/or systems the referenced Airworthiness
Directive shall be applied expires if the AD is not embodied within specified terms.
Nota 2
Per ulteriori informazioni contattare ENAC Direzione Regolazione Navigabilità e Operazioni
For further information contact ENAC Airworthiness and Operations Regulation Division
email : [email protected]
fax :+390644185731
EASA AD No.: 2012-0139
EASA
AIRWORTHINESS DIRECTIVE
AD No.: 2012-0139
Date: 27 July 2012
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].
Design Approval Holder’s Name :
Type/Model designation(s) :
AgustaWestland S.p.A.
A119 helicopters
TCDS Number:
EASA.R.005
Foreign AD:
Not applicable
Revision:
None
ATA 32
Landing Gear – Skid Landing Gear Forward Crossbeam Assembly
– Inspection / Replacement
Manufacturer(s):
AgustaWestland S.p.A (formerly Agusta S.p.A.), AgustaWestland Philadelphia
Corporation (formerly Agusta Aerospace Corporation).
Applicability:
A119 helicopters, all serial numbers (S/N) up to S/N 14700 inclusive, except
those having Agusta Bollettino N° 119-26 embodied in service.
Reason:
Operators of Agusta A119 helicopters, configured with hoist and/or external
loads fixed to the skid landing gear, reported cases of fracture of the forward
(fwd) crossbeam assembly in correspondence of the right side clamp
assembly external fixing rivets line.
The subsequent technical investigations concluded that the fracture reported
on the fwd crossbeam assembly was due to fatigue.
This condition, if not detected and corrected, could lead to damage to the
helicopter and injury to the occupants.
To address this unsafe condition, AgustaWestland issued BT N° 119-48.
For the reasons described above, this AD requires repetitive inspections of the
crossbeam assembly Part Number (P/N) 109-0570-04-101 for detecting cracks
and, depending on findings, accomplishment of the applicable corrective
actions.
Effective Date:
10 August 2012
CAP.00110-001 © European Aviation Safety Agency. All rights reserved.
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
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EASA AD No.: 2012-0139
Required Action(s)
and Compliance
Time(s):
Ref. Publications:
Required as indicated, unless already accomplished:
(1)
Within 50 Flight Hours (FH) or 4 months, whichever occurs first after the
effective date of this AD, and thereafter, at intervals not to exceed 200
FH, inspect the crossbeam assembly Part Number (P/N) 109-0570-04101 in accordance with the instructions of AgustaWestland BT 119-48.
(2)
If, during any inspection as required by paragraph (1) of this AD, a
cracked crossbeam assembly is detected, before next flight, replace the
affected part with a serviceable part in accordance with the instructions
of AgustaWestland BT 119-48.
(3)
Replacement of a crossbeam assembly with a serviceable part as
required by paragraph (2) of this AD does not constitutes terminating
action for the repetitive inspections required by paragraph (1) of this AD.
AgustaWestland BT 119-48, original issue dated 26 July 2012.
The use of later approved revisions of this document 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 required action and the risk allowance have granted the issuance of a
Final AD with Request for Comments, postponing the public consultation
process after publication.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail: [email protected].
4. For any question concerning the technical content of the requirements in
this AD, please contact AgustaWestland
E-mail: [email protected] .
CAP.00110-001 © European Aviation Safety Agency. All rights reserved.
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
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