2016-15-01: 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 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 airworthiness directive (AD): 2016-15-01 Airbus: Amendment 39-18592. Docket No. FAA-2016-3993; Directorate Identifier 2015-NM-065-AD. (a) Effective Date This AD is effective August 26, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4- 103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.(3) Airbus Model A300 B4-605R and B4-622R airplanes. (4) Airbus Model A300 F4-605R and F4-622R airplanes. (5) Airbus Model A300 C4-605R Variant F airplanes. (6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Reason This AD was prompted by reports of partial loss of no-back brake (NBB) efficiency on the trimmable horizontal stabilizer actuator (THSA). We are issuing this AD to prevent loss of THSA NBB efficiency, which, in conjunction with the inability of the power gear to keep the ball screw in its last commanded position, could lead to an uncommanded movement of the horizontal stabilizer, possibly resulting in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Affected THSAs THSAs affected by the requirements of this AD have part numbers (P/Ns) 47142-403, 47142-413, 47142-414, and 47142-423. Note 1 to paragraph (g) of this AD: FAA AD 2011-15-08, Amendment 39-16755 (76 FR 42029, July 18, 2011), requires installation of three secondary retention plates for the gimbal bearings on the THSA upper primary attachment, which involved a THSA part number change from the -300 series to the -400 series. Note 2 to paragraph (g) of this AD: The life limits specified in Part 4 of the airworthiness limitations section are still relevant for the affected THSA. This AD addresses a replacement limit for the NBB disks installed on the THSA, not the life limit for the THSA itself. (h) Inspection for Affected THSAs, Flight Cycles, and THSA Replacement Before each date and before exceeding the corresponding THSA flight-cycle limits specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD; and before exceeding the flight-cycle limit corresponding to each date as specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, do the actions specified in paragraph (i) of this AD. (1) Do an inspection of the THSA to determine the part number and serial number. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the THSA can be conclusively determined from that review. (2) Do an inspection of the airplane maintenance records to determine the flight cycles accumulated on each affected THSA since first installation on an airplane, or since last NBB replacement, whichever is later. If no maintenance records conclusively identifying the last NBB disk replacement are available, the flight cycles accumulated since first installation of the THSA on an airplane apply. (i) THSA Replacement By each date specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, for those affected THSAs having reached or exceeded the corresponding number of flight cycles specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, replace the THSA with a serviceable unit, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-27-6070, dated February 17, 2015; or Airbus Service Bulletin A310-27-2106, dated February 17, 2015, as applicable. (j) Compliance Dates and THSA Flight-Cycle Limits Paragraphs (j)(1), (j)(2), and (j)(3) of this AD specify compliance dates and THSA flight-cycle limits for accomplishing the actions required by paragraphs (h) and (i) of this AD. (1) As of 30 days after the effective date of this AD: The affected THSA flight-cycle limit is 30,000 flight cycles since first installation of the THSA on an airplane, or since last NBB replacement, whichever is later. (2) As of February 1, 2017: The affected THSA flight-cycle limit is 20,000 flight cycles since first installation of the THSA on an airplane, or since last NBB replacement, whichever is later. (3) As of February 1,2019: The affected THSA flight-cycle limit is 14,600 flight cycles since first installation of the THSA on an airplane, or since last NBB replacement, whichever is later. (k) Serviceable THSA Definition For the purpose of this AD, a serviceable THSA is a unit identified in paragraph (k)(1) or (k)(2) of this AD. (1) A THSA identified in paragraph (g) of this AD that, as of each date specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, has not exceeded the flight-cycle limits specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD since first installation of the THSA on an airplane, or since the last NBB disk replacement, whichever is later. (2) A THSA with a different part number (e.g., a THSA that is not identified in paragraph (g) of this AD) that is not affected by the requirements of this AD. (l) THSA Replacements As of each date and before exceeding the flight-cycle limit corresponding to each date [[Page 47699]] specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD: Replace each affected THSA with a serviceable unit, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-27-6070, dated February 17, 2015; or Airbus Service Bulletin A310-27-2106, dated February 17, 2015. (m) Parts Installation Limitation Before each date specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, an operator may install an affected THSA on an airplane, provided that the unit has not exceeded the corresponding number of flight cycles specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, since first installation on an airplane, or since last NBB replacement, whichever is later. (n) 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 proceduresfound 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 Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-2125; fax: 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (o) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0081, dated May 7, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA- 2016-3993. (p) 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 A300-27-6070, dated February 17, 2015. (ii) Airbus Service Bulletin A310-27-2106, dated February 17, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; 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.