EASA AD 2010-0254

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SEKCE TECHNICKÁ PŘÍKAZ K ZACHOVÁNÍ LETOVÉ ZPŮSOBILOSTI Číslo: EASA AD 2010-0254 Ruší EASA AD 2009-0065R1 Účinnost od: 20. prosince 2010 Eurocopter Deutschland GmbH EC 135, EC 635 Tento PZZ je vydáván pro výrobek transferovaný pod působnost EASA. Na základě rozhodnutí EASA je následující Příkaz k zachování letové způsobilosti závazný pro všechny výrobky provozované v EU na které se daný PZZ vztahuje. Provedení PZZ, který se vztahuje podle typu a výrobního čísla na výrobek je pro provozovatele/vlastníka letadla zapsaného do leteckého rejstříku závazné. Neprovedením PZZ ve stanoveném termínu dojde ke ztrátě letové způsobilosti výrobku. Poznámky: - Provedení tohoto PZZ musí být zapsáno do provozní dokumentace letadla. - Případné dotazy týkající se tohoto PZZ adresujte na ÚCL sekce technická. - Pokud to vyžaduje povaha tohoto PZZ, musí být zapracován do příslušné části dokumentace pro obsluhu, údržbu a opravy letadla. ÚŘAD PRO CIVILNÍ LETECTVÍ, Letiště Ruzyně, 160 08 Praha 6 fax: +420 220 561 823 • telefon: +420 225 421 111 • www.ucl.cz • email: podatelna@caa. EASA AD No.: 2010-0254 EASA Form 110 Page 1/4 EASA AIRWORTHINESS DIRECTIVE AD No.: 2010-0254 Date: 06 December 2010 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 : Eurocopter Deutschland GmbH Type/Model designation(s) : EC 135 and EC 635 helicopters TCDS Number : EASA.R.009 Foreign AD : Not applicable Supersedure : This AD supersedes EASA AD 2009-0065R1 dated 08 September 2009. ATA 53 Fuselage – Rear Structure / Tail Boom – Pre-Flight Check / Inspection / Modification Manufacturer(s): Eurocopter Deutschland GmbH, Eurocopter ESPANA S.A. Applicability: EC 135 P1(CDS), EC 135 P1(CPDS), EC 135 P2(CPDS), EC 135 P2+, EC 135 T1(CDS), EC 135 T1(CPDS), EC 135 T2(CPDS), EC 135 T2+, EC 635 T1(CPDS), EC 635 P2+ and EC 635 T2+ helicopters, all serial numbers. Reason: During a pre-flight check on an EC135 helicopter, a crack was detected on the ring frame that connects the tail rotor Fenestron housing to the rear structure tube (tail boom). The crack ran alongside one rivet row over about one third of the circumference of the ring frame. This condition, if not corrected, could lead to crack propagation remaining undetected, possibly resulting in loss of the Fenestron structure and consequent loss of control of the helicopter. To address and correct this unsafe condition, EASA issued Emergency AD 2008-0190-E that required the amendment of the basic Flight Manual (FLM), the accomplishment of repetitive pre-flight checks, a one-time inspection and corrective actions. Based on in-service feedback, Eurocopter Deutschland (ECD) revised Alert Service Bulletin (ASB) EC135-53A-022 to introduce a repetitive visual inspection. For the reason described above, EASA AD 2009-0065 was issued, retaining the requirements of EASA AD 2008-0190-E, which was superseded, expanding the applicability to include EC 135 helicopters manufactured in Spain and adding a repetitive inspection of the rear fuselage structure (tail boom) area for cracks. ECD subsequently developed a modification (reinforcement) of the aft ring frame, including Part Number (P/N) change, for both production and in-service application. Consequently, AD 2009-0065 was revised to remove helicopters EASA AD No.: 2010-0254 EASA Form 110 Page 2/4 from the Applicability of the AD that have a new or modified aft ring frame P/N L535H2120302 installed and to introduce modification (and re-identification) of the aft ring frame as optional terminating action for the required repetitive checks and inspections. More recently, EASA have determined that, to ensure an adequate safety level, the interval of the visual inspection must be reduced from 100 flight Hours (FH) to 25 FH. In addition, the optional terminating action is to be made mandatory. For the reasons described above, this new AD retains the requirements of EASA AD 2009-0065R1, which is superseded, reduces the interval of the visual inspection and requires modification (and re-identification) of the aft ring frame as terminating action for the repetitive checks and inspections. Effective Date: 20 December 2010 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: For helicopters that have an aft ring frame P/N L535A3501230 installed: (1) Before next flight after 27 March 2009 [the effective date of AD 2009- 0065], amend the FLM, Section 4 Pre-Flight Check, by inserting page 6 or 7, as applicable to helicopter Model, of ECD EC135 ASB EC135-53A-022 into the FLM, and inform the flight crew accordingly. Amending the FLM to the revision level as indicated in Appendix 1 of this AD, as applicable to helicopter Model, is acceptable to comply with the requirement of paragraph (1) of this AD. (2) Before next flight after 27 March 2009 [the effective date of AD 2009-0065] and thereafter before each first flight of a day, accomplish the visual check of the rear structure tube in accordance with the instructions of ECD ASB EC135-53A-022. The pilot is allowed to accomplish this check as part of the regular pre-flight checks. (3) Within 25 FH (+ 5 FH tolerance) or within 100 FH since the last inspection