2014-15-09: Flight Controls

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 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 airworthiness directive (AD): 2014-15-09 Airbus: Amendment 39-17911. Docket No. FAA-2014-0228; Directorate Identifier 2013-NM-216-AD. (a) Effective Date This AD becomes effective September 5, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330-201, -202, -203, -223, - 223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; Model A340-211, -212, -213, -311, -312, and -313 airplanes; and Model A340-541 and -642 airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by reassessment of an unsafe condition related to MZ-type spoiler servo-controls (SSCs) that did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. This reassessment resulted in the determination that performing repetitive operational tests of all SSC types is necessary. We are issuing this AD to detect and correct loss of the hydraulic locking function during take-off, which, in combination with one inoperative engine, could result in reduced controllability of the airplane. [[Page 44666]] (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) Repetitive Operational Tests (1) At the time specified in paragraph (g)(2) of this AD:Accomplish an operational test of the hydraulic locking function on each SSC (any type), when fitted on the Blue or Yellow hydraulic circuits, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Repeat the operational test thereafter at intervals not to exceed 48 months. (i) Airbus Service Bulletin A330-27-3195, Revision 01, dated February 6, 2014 (for Model A330-200 Freighter, A330-200 and -300 series airplanes). (ii) Airbus Service Bulletin A340-27-4188, Revision 01, dated February 6, 2014 (for Model A340-200, and -300 series airplanes). (iii) Airbus Service Bulletin A340-27-5059, Revision 01, dated February 6, 2014 (for Model A340-500 and -600 series airplanes). (2) At the latest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD, do the operational test specified in paragraph (g)(1) of this AD. (i) Within 48 months sincefirst flight of the airplane. (ii) Within 48 months since accomplishing the most recent operational test, as specified in the applicable Airbus All Operators Telex (AOT) A330-27A3185; or AOT A340-27A4181; both dated January 4, 2012. These AOTs were incorporated by reference in AD 2012-25-10, Amendment 39-17291 (77 FR 76228, December 27, 2012). (iii) Within 24 months after the effective date of this AD. (h) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, which is not incorporated by reference in this AD. (i) Airbus Service Bulletin A330-27-3195, dated December 7, 2012. (ii) Airbus Service Bulletin A340-27-4188, dated December 7, 2012. (iii) Airbus Service Bulletin A340-27-5059, dated April 10, 2013. (i) Replacement of Affected SSCs If, during any operational test required by paragraph (g)(1) of this AD, the hydraulic locking function of an SSC fails the test, before further flight, replace the affected SSC with a serviceable part, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. (j) No Terminating Action Doing the replacement required by paragraph (i) of this AD is not terminating action for the repetitive operational tests required by paragraph (g)(1) of 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: [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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Ifapproved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013- 0251 dated October 15, 2013; Correction dated October 16, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014- 0228-0002. (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 Service Bulletin A330-27-3195, Revision 01, dated February 6, 2014. (ii) Airbus Service Bulletin A340-27-4188, Revision 01, dated February 6, 2014. (iii) Airbus Service Bulletin A340-27-5059, Revision 01, dated February 6, 2014. (3) For service information identified in this AD, 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 this 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.