2013-14-04: Powerplant

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 adding the following new AD: 2013-14-04 Airbus: Amendment 39-17509. Docket No. FAA-2013-0212; Directorate Identifier 2012-NM-116-AD. (a) Effective Date This airworthiness directive (AD) becomes effective December 19, 2013. (b) Affected ADs This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 4, 2006). (c) Applicability This AD applies to Airbus Model A330-223F, -223, -321, -322, and -323 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) ReasonThis AD was prompted by fatigue load analysis that determined that certain pylon bolts inspection interval must be reduced. We are issuing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in-flight, and damage to the airplane. [[Page 68354]] (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) Torque Check and Replacement (1) Within the compliance times specified in table 1 to paragraph (g) of this AD, as applicable to airplane model and utilization, do a torque check to determine if there are any loose or broken forward engine mount bolts (4 positions/engine) on both engines, and repeat that torque check at intervals not to exceed the values defined in table 1 to paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. For the purposes of table 1 to paragraph (g) of this AD, the average flight time (AFT) is defined as a computation of the number of flight hours divided by the number of flight cycles accumulated since last torque check or since the airplane's first flight, as applicable. Table 1 to Paragraph (g) of This AD ---------------------------------------------------------------------------------------------------------------- Flight cycles accumulated on the effective date of this AD since last torque check performed as Airplane models specified in Pratt & Compliance time Torque check interval Whitney Alert Service (not to exceed) Bulletin PW4G-100-A71- 32, or since airplane first flight, as applicable ---------------------------------------------------------------------------------------------------------------- For Model A330-223,-321, -322, and - 0-1,850................ Within 2,350 flight cycles 2,350 flight cycles 323 airplanes with AFT more than since the last torque or 24,320 flight 132 minutes. check as specified in hours, whichever Pratt & Whitney Alert occurs first. Service Bulletin PW4G-100- A71-32, or since airplane first flight, as applicable. For Model A330-223, -321, -322, and 1,851-2,700............ Within 500 flight cycles 2,350 flight cycles -323 airplanes with AFT more than after the effective date or 24,320 flight 132 minutes. of this AD without hours, whichever exceeding 2,700 flight occurs first. cycles since last torque check as specified in Pratt & Whitney Alert Service Bulletin PW4G-100- A71-32, or since airplane first flight, as applicable; or within 3 monthsafter the effective date of this AD; whichever occurs later. For Model A330-321,-322, and -323 0-1,450................ Within 1,950 flight cycles 1,950 flight cycles airplanes with AFT equal or less since the last torque or 20,210 flight than 132 minutes; and for Model check performed as hours, whichever A330-321, -322, and -323 airplanes specified in Pratt & occurs first. on which the AFT is not calculated Whitney Alert Service on a regular basis. Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable. For Model A330-321, -322, and -323 1,451-2,700............ Within 500 flight cycles 1,950 flight cycles airplanes with AFT equal or less after the effective date or 20,210 flight than 132 minutes; and for Modelof this AD without hours, whichever A330-321,-322, and -323 airplanes exceeding 2,700 flight occurs first. on which the AFT is not calculated cycles since last torque on a regular basis. check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable; or within 3 months after the effective date of this AD; whichever occurs later. For Model A330-223F airplanes...... Not applicable......... Within 2,140 flight cycles 2,140 flight cycles or 6,600 flight hours, or 6,600 flight whichever occurs first hours, whichever since the last torque occurs first. check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable. ---------------------------------------------------------------------------------------------------------------- (2) If any loose or broken bolt is detected during the check required by paragraph (g)(1) of this AD, before further flight, replace all four forward engine mount bolts and associated nuts, on the engine where the loose or broken bolt was detected, with new bolts and nuts, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. (3) Replacement of bolts and nuts as required by paragraph (g)(2) of this AD is not terminating action for the repetitive torque checks required by paragraph (g)(1) of this AD. (h) Compliance With AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 4, 2006) Doing the actions required by paragraph (g) of this AD constitutes compliance with the requirements specified in paragraph (g) of AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 4, 2006). (i) Parts Installation Prohibition As of the effective date of this AD, no person may install any INCO718 material, forward mount pylon bolt having Pratt & Whitney part number 54T670 on any airplane. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g)(1) and (g)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Mandatory Service Bulletin A330-71-3028, dated December 16, 2011, which is not incorporated by reference in this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, 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: 9-ANM-116- [[Page 68355]] [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 returnedto service. (l) Related Information (1) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2012-0094, dated May 31, 2012, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0212-0002. (2) Service information identified in this AD that is not incorporated by reference may be viewed at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. (ii) Reserved. (3) For service information identified in thisAD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (4) You may view copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.