2012-19-02: Engine Exhaust

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD) 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005), and adding the following new AD: 2012-19-02 Airbus: Amendment 39-17197. Docket No. FAA-2012-0671; Directorate Identifier 2011-NM-096-AD. (a) Effective Date This airworthiness directive (AD) becomes effective October 23, 2012. (b) Affected ADs This AD supersedes AD 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005). (c) Applicability This AD applies to all Airbus Model A330-243, -243F, -341, -342 and -343 airplanes, certificated in any category. (d) SubjectAir Transport Association (ATA) of America Code 78, Engine Exhaust. (e) Reason This AD was prompted by new life limits on certain thrust reverser C-duct assemblies. We are issuing this AD to prevent fatigue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, which could result in separation of a thrust reverser from the airplane, and consequent reduced controllability of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) C-duct Assembly Removal At the applicable compliance time specified in table 1 to paragraph (g) of this AD: Remove the applicable C-duct assemblies of the left- and right-hand thrust reversers, in accordance with a method approved by either the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA)(or its delegated agent). Thereafter, for any C-duct assembly of the left- and right-hand thrust reversers installed after the effective date of this AD, before the accumulation of the applicable total flight cycles specified in table 1 to paragraph (g) of this AD: Remove the C-duct assembly, in accordance with a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent). Table 1 to Paragraph (g) of This AD--Part Removal Thresholds ------------------------------------------------------------------------ ------------------------------------------------------------------------ Part No.-- Compliance times at the later of the times specified-- ------------------------------------------------------------------------ HDTR3410L, HDTR3410R, Before the Within 3 months HDTR3411L, HDTR3411R, accumulation of after the effective HDTR3412R, HDTR3413R. 10,000 total flightdate of this AD. cycles since the first installation of C[dash]duct on the airplane. HDTR3414L, HDTR3416R, Before the Within 3 months HDTR3417R that have been accumulation of after the effective modified in service as 10,000 total flight date of this AD. specified in Airbus cycles since the Mandatory Service Bulletin first installation A330[dash]78[dash]3010 or of C[dash]duct on Rolls-Royce Service the airplane. Bulletin RB.211-78-C899 at 7,200 total flight cycles or more since first installation on an airplane. HDTR3414L, HDTR3416R, Before the Within 3 months HDTR3417R that have been accumulation of after the effective modified in production by 25,000 total flight date of this AD. Airbus Modification 47316 cycles since the or that have been modified first installation in service as specified in of C[dash]duct on Airbus Mandatory Service the airplane. Bulletin A330[dash]78[dash]3010 or Rolls-Royce Service Bulletin RB.211-78-C899, before the accumulation of 7,200 total flight cycles since first installation on an airplane. [[Page 57486]] HDTR3412L, HDTR3416L, Before the Within 3 months HDTR3417L, HDTR3414R, accumulation of after the effective HDTR3419R, HDTR3420R. 25,000 total flight date of this AD. cycles since the first installation of C[dash]duct on the airplane. HDTR3413L, HDTR3415R, Before the Within 3 months HDTR3415L, HDTR3418R. accumulation of after the effective 40,000 total flight date of this AD. cycles since the C[dash]duct was new. ------------------------------------------------------------------------ (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs):The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227- 1138; fax (425) 227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (i) Related Information Refer to MCAI EASA Airworthiness Directive 2011-0018, dated February 3, 2011; for related information. (j) Material Incorporated by Reference None.