Airworthiness Directives; Airbus Airplanes, 56859-56865 [2017-25557]

Download as PDF 56859 Rules and Regulations Federal Register Vol. 82, No. 230 Friday, December 1, 2017 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0476; Product Identifier 2016–NM–110–AD; Amendment 39–19111; AD 2017–24–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: jstallworth on DSKBBY8HB2PROD with RULES Examining the AD Docket We are superseding Airworthiness Directive (AD) 2014–08– 01, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014–08–01 required an inspection for part numbers of the interconnecting struts and, for affected interconnecting struts, identification of the part and serial numbers of the associated target and proximity sensors and replacement or re-identification of the flap interconnecting strut if necessary. This AD continues to require an inspection to verify the interconnecting strut part number. This AD also provides a new compliance time and an additional inspection for previously inspected airplanes. This AD was prompted by an investigation that showed that when a certain combination of target/proximity sensor serial numbers is installed on a flap interconnecting strut, a ‘‘target FAR’’ signal cannot be detected when reaching the mechanical end stop of the interconnecting strut. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 5, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 5, 2018. SUMMARY: VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 26, 2014 (79 FR 9398, February 19, 2014). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 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. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0476. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0476; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014–08–01, Amendment 39–17825 (79 FR 23900, April 29, 2014) (‘‘AD 2014–08–01’’). AD 2014–08–01 applied to all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Federal Register on May 19, 2017 (82 FR 22918). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0113, dated June 15, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states: The flap interconnecting strut is a safety device of the High Lift System which acts as an alternative load path from one flap surface to another in case of a flap drive system disconnection. In such a failure case, the installed proximity sensors provide information to the slat flap control computer (SFCC) and the operation of the flap drive system is inhibited. An engineering investigation showed that, when a certain combination of target/sensor serial number (s/n) is installed on a flap interconnecting strut, a ‘‘target FAR’’ signal cannot be detected when reaching the mechanical end stop of the interconnecting strut. This condition, if not corrected, could cause a flap down drive disconnection to remain undetected, due to an already-failed interconnecting strut sensor, potentially resulting in asymmetric flap panel movement and consequent loss of control of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 27–1206 and SB A320–57–1164, to provide identification and replacement instructions for struts that have a certain target/sensor s/ n combination installed. Aeroplanes on which modification (mod) 27956 had been accomplished in production were identified as not affected by the unsafe condition. Consequently, EASA issued [EASA] AD 2012–0012 [which corresponds to FAA AD 2014–08–01] to require accomplishment of these inspections and corrective actions. Since that [EASA] AD was issued, Airbus has informed EASA about a batch of aeroplanes that were delivered with pre-mod 27956 Part Number (P/N) flap interconnecting strut(s) installed, but declared to be in post-mod configuration in the Aircraft Inspection Report. Airbus SB A320–57–1202 has been issued to provide instructions to verify the interconnecting strut P/N, and to update aircraft documentation. In addition, to ensure that all pre-mod parts are checked and corrected as required, SB A320–27–1206 was revised to include a wider range of P/N of affected interconnecting struts. For the reasons described above, this [EASA] AD retains the requirements of EASA E:\FR\FM\01DER1.SGM 01DER1 56860 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations AD 2012–0012, which is superseded, expands the Applicability [adds affected part numbers], changes the compliance time and requires an additional inspection for aeroplanes that have already been inspected. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0476. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. United Airlines and the Air Line Pilots Association, International supported the NPRM. Request To Add Additional Identification Steps Delta Airlines (DAL) requested that additional identification steps be required in the NPRM to ensure that the affected parts are correctly identified. DAL stated that figure 1 to paragraphs (g) and (h) of the proposed AD contains part numbers for affected interconnecting struts. DAL commented that a review of its records from inspections conducted during compliance with AD 2014–08–01 determined that other part numbers were possible. DAL stated that it has had at least one instance of a part with the part number D5757032200000A. DAL stated that figure 2 to paragraphs (i)(2), (k), and (l) of the proposed AD adds the provision that additional alphanumeric characters may exist. DAL commented that while the NPRM removes some of the ambiguity that existed in AD 2014–08–01, a review of Airbus’s Aircraft Illustrated Parts Catalog (AIPC) does not show any parts with a ‘‘letter’’ suffix. DAL provided a photo that showed that the part number appears to ‘‘wrap’’ (to the next line) on the part. DAL stated that this ‘‘wrapping’’ condition has led to confusion in identifying the parts. DAL stated that per the Airbus AIPC Front Matter, the 13th, 14th, and 15th characters are controlled in specific ways. DAL also stated that the 13th and 14th characters are expected to be ‘‘00’’ and are used to fill out 12-digit base numbers on the part installed during production. DAL stated that the 15th character is a paint code designator and found the use of a paint code designator unusual on a part that is not viewable or expected to be painted to match an air carrier paint scheme. DAL commented that it believes the AD should be updated to show 00A, 00B, or the list of true possibilities, and the XXX allowance creates a significant number of possible part numbers that DAL must identify as prohibited. We agree to clarify the requirement to identify affected parts. Regarding the characters in the part number, identifying the last three characters are not required to identify a discrepant part; only the first twelve base numbers are required. Therefore, we do not agree to revise this AD to include a complete list of all possible combinations of these characters. We acknowledge the commenter’s concern about the ‘‘wrapping’’ condition for part identification. However, in the photo provided by the commenter only the last three characters are ‘‘wrapped.’’ As stated previously, the last three characters are not required to identify a discrepant part. Formatting Change to a Figure Figure 3 to paragraph (k)(1) of this AD has been reformatted to clarify affected manufacturer serial numbers. Records Review We have determined that a review of maintenance records is acceptable for complying with the actions specified in paragraphs (i)(1) and (i)(2) of this AD, provided the part number of the installed interconnecting struts and the part number and the serial number of the associated target and proximity sensor can be conclusively determined from that review. We have revised paragraph (i) of this AD accordingly. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–27–1206, Revision 02, dated November 2, 2015. The service information describes procedures for an inspection to determine the part number of the installed interconnecting struts and the part number and serial number of the associated target and proximity sensors, and procedures for replacement and re-identification of the interconnecting struts. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 1,032 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Cost per product Inspection and replacement (retained actions from AD 2014–08–01). Inspection and replacement (new action) ....... jstallworth on DSKBBY8HB2PROD with RULES Labor cost 8 work-hours × $85 per hour = $680 ............. $0 $680 $701,760 15 work-hours × $85 per hour = $1,275 ........ 0 1,275 1,315,800 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 Parts cost Cost on U.S. operators Action Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with E:\FR\FM\01DER1.SGM 01DER1 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: jstallworth on DSKBBY8HB2PROD with RULES PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2014–08–01, Amendment 39–17825 (79 FR 23900, April 29, 2014), and adding the following new AD: ■ 2017–24–07 Airbus: Amendment 39–19111; Docket No. FAA–2017–0476; Product Identifier 2016–NM–110–AD. (a) Effective Date This AD is effective January 5, 2018. (b) Affected ADs This AD replaces AD 2014–08–01, Amendment 39–17825 (79 FR 23900, April 29, 2014) (‘‘AD 2014–08–01’’). (c) Applicability This AD applies to Airbus Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 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 an investigation that showed that when a certain combination of target/proximity sensor serial numbers is installed on a flap interconnecting strut, a ‘‘target FAR’’ signal cannot be detected when reaching the mechanical end stop of the interconnecting strut. We are issuing this AD to prevent an undetected flap down drive disconnection due to an already-failed interconnecting strut sensor, which could result in asymmetric flap panel movement and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection To Determine the Part Number of the Interconnecting Struts, With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2014–08–01, with revised service information. Within 8,000 flight hours after March 26, 2014 (the effective date of AD 2014–03–08, Amendment 39–17745 (79 FR 9398, February 19, 2014) (‘‘AD 2014–03–08’’)), inspect to determine the part number of the interconnecting struts installed on both the left-hand (LH) and right-hand (RH) wings of the airplane, in accordance with the Accomplishment Instructions of Airbus PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 56861 Service Bulletin A320–27–1206, Revision 01, dated October 10, 2011; or Airbus Service Bulletin A320–27–1206, Revision 02, dated November 2, 2015. A review of the airplane maintenance records is acceptable for determining the part number of the installed interconnecting struts, in lieu of the inspection, if the part number of the installed interconnecting struts, and the part number and the serial number of the associated target and proximity sensor, can be conclusively determined from that review. Accomplishment of the requirements of paragraph (i) of this AD terminates the requirements of this paragraph. (1) Airplanes on which Airbus Modification 27956 has been embodied in production, and on which no interconnecting strut has been replaced with a strut having a part number specified in figure 1 to paragraphs (g) and (h) of this AD since the airplane’s first flight: No further work is required by paragraph (g) of this AD. (2) If, during the inspection required by paragraph (g) of this AD, any interconnecting strut is installed with a part number specified in figure 1 to paragraphs (g) and (h) of this AD: Within 8,000 flight hours after March 26, 2014 (the effective date of AD 2014–03–08), determine the part number and the serial number of the associated target and proximity sensor. (i) For airplanes having conditions specified in paragraphs (g)(2)(i)(A), (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this AD: Before further flight, replace the interconnecting strut with a serviceable unit, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, Revision 01, dated October 10, 2011; or Airbus Service Bulletin A320–27– 1206, Revision 02, dated November 2, 2015. For the purposes of paragraph (g) of this AD, a serviceable interconnecting strut is a unit that has been determined to be in compliance with the requirements of paragraph (g) of this AD. (A) A target part number (P/N) ABS0121– 13 or P/N 8–536–01; and (B) A target serial number lower than 1600, or a target serial number that is unreadable; and (C) A proximity sensor having P/N ABS0121–31 or P/N 8–372–04; and (D) A proximity sensor having a serial number between C59198 and C59435, or a serial number (S/N) C500000 or higher. (ii) For a target having S/N 1600 or higher and target P/N ABS0121–13 or P/N 8–536– 01: Within 8,000 flight hours after March 26, 2014 (the effective date of AD 2014–03–08), re-identify the interconnecting strut, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, Revision 01, dated October 10, 2011; or Airbus Service Bulletin A320–27– 1206, Revision 02, dated November 2, 2015. BILLING CODE 4910–13–P E:\FR\FM\01DER1.SGM 01DER1 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations (h) Retained Parts Installation Prohibition, With No Changes jstallworth on DSKBBY8HB2PROD with RULES This paragraph restates the requirements of paragraph (h) of AD 2014–08–01, with no changes. As of March 26, 2014 (the effective date of AD 2014–03–08), no person may install an interconnecting strut with a part number specified in figure 1 to paragraphs (g) and (h) of this AD, on any airplane, except for parts identified in paragraph (g)(2)(ii) of this AD, provided that the actions in paragraph (g)(2)(ii) are done. As of the effective date of this AD, comply with the requirements of paragraph (l) of this AD in lieu of the requirements of this paragraph. VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 (i) New Requirements of This AD: Inspection To Determine the Part Number of the Interconnecting Struts and the Part Number and Serial Number of the Associated Target and Proximity Sensor Within 24 months after the effective date of this AD, accomplish the actions specified in paragraphs (i)(1) and (i)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, Revision 02, dated November 2, 2015. Accomplishment of the actions specified in this paragraph terminates the requirements of paragraph (g) of this AD. In lieu of doing the actions specified in paragraphs (i)(1) and (i)(2) of this AD, a review of the airplane maintenance records is acceptable for determining the part number of the installed interconnecting struts and the PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 part number and the serial number of the associated target and proximity sensor, if the part number and serial numbers can be conclusively determined from that review. (1) Inspect to determine the part number of the interconnecting struts installed on both the LH and RH wings on the airplane. (2) If an interconnecting strut is installed with a part number specified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, identify the part number and the serial number of the associated target and proximity sensor; and for the target and proximity sensor part number and serial number combination specified in paragraph (j) of this AD, within the compliance times specified in paragraph (j) of this AD, do the actions specified in paragraph (j) of this AD for that interconnecting strut. E:\FR\FM\01DER1.SGM 01DER1 ER01DE17.000</GPH> 56862 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, Revision 02, dated November 2, 2015. (B) If any discrepancy is found, before further flight, replace the interconnecting strut with a serviceable unit, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1206, Revision 02, dated November 2, 2015. (2) If the target serial number is 1600 or higher (with any proximity sensor part number and serial number): Within 24 months after the effective date of this AD, re-identify the interconnecting strut, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, Revision 02, dated November 2, 2015. (k) Additional Provisions of This AD (1) Airplanes on which Airbus Modification 27956 has been embodied in production, and on which no interconnecting strut with a part number identified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD has been installed since the airplane’s first flight, are not affected by the requirements of PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 paragraph (i) of this AD, except for those manufacturer serial numbers specified in figure 3 to paragraph (k)(1) of this AD. Airplanes having manufacturer serial numbers specified in figure 3 to paragraph (k)(1) of this AD are affected by the requirements of paragraph (i) of this AD. (2) For an airplane that has already been inspected before the effective date of this AD as specified in the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, dated January 28, 2011; or Revision 01, dated October 10, 2011: Within the compliance time specified in paragraph (i) of this AD, accomplish the additional work specified in and in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1206, Revision 02, dated November 2, 2015, unless it is determined that no interconnecting strut with a part number specified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD is installed on that airplane. A review of airplane maintenance records is acceptable to make this determination, provided the part number can be conclusively identified from that review. E:\FR\FM\01DER1.SGM 01DER1 ER01DE17.001</GPH> jstallworth on DSKBBY8HB2PROD with RULES (j) New Requirements of This AD: Replacement or Re-Identification (1) If the target serial number is lower than 1600 or is unreadable, and the proximity sensor part number is P/N ABS0121–31 or P/N 8–372–04 with a serial number between S/N C59198 and C59435, or S/N C500000 or higher: Before further flight, do the actions specified by paragraph (j)(1)(i) or (j)(1)(ii) of this AD. For the purposes of paragraph (j) of this AD, a serviceable interconnecting strut is a unit that has been determined to be in compliance with the requirements of paragraphs (i) and (j) of this AD. (i) Replace the interconnecting strut with a serviceable unit, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1206, Revision 02, dated November 2, 2015. (ii) Do a general visual inspection of the flap down drive to detect discrepancies, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1206, Revision 02, dated November 2, 2015. (A) If no discrepancy is found, within 50 flight cycles after the inspection, replace the interconnecting strut with a serviceable unit, 56863 56864 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations Figure 3 to paragraph (k)(l) of this AD -Additional affected manufacturer serial numbers Airplane model Affected manufacturer serial numbers 1857 1861 1865 1867 1868 1871 1873 1874 1877 1879 1883 1885 1888 1889 1891 1892 1894 1895 1896 1898 1899 1900 1902 1903 1904 1906 1907 1909 1910 1911 1913 1914 1915 1917 1918 1920 1922 1924 1927 1929 1931 1933 1935 1937 1940 1942 1944 1945 1948 1949 1951 1954 1957 1958 1961 1964 1965 1968 1969 1973 1975 1979 1981 1983 1987 1819 1820 1824 1826 1831 1833 1837 1839 1841 1844 1846 1851 1853 1855 1863 1866 1870 1872 1875 1876 1880 1882 1884 1886 1890 1893 1897 1901 1908 1912 1916 1923 1925 1934 1936 1938 1943 1947 jstallworth on DSKBBY8HB2PROD with RULES BILLING CODE 4910–13–C (m) Credit for Previous Actions (l) New Requirement of This AD: Parts Installation Limitations As of the effective date of this AD, no person may install, on any airplane, an interconnecting strut with a part number specified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, unless it is in compliance with the requirements of this AD. This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before March 26, 2014 (the effective date of AD 2014–03– 08), using Airbus Service Bulletin A320–27– 1206, dated January 28, 2011, and if additional work since March 26, 2014 (the effective date of AD 2014–03–08) has been VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 accomplished using Airbus Service Bulletin A320–27–1206, Revision 01, dated October 10, 2011. (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International E:\FR\FM\01DER1.SGM 01DER1 ER01DE17.002</GPH> A319 series airplanes 1860 1864 A320 series airplanes 1858 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations (3) The following service information was approved for IBR on January 5, 2018. (i) Airbus Service Bulletin A320–27–1206, Revision 02, dated November 2, 2015. (ii) Reserved. (4) The following service information was approved for IBR on March 26, 2014 (79 FR 9398, February 19, 2014). (i) Airbus Service Bulletin A320–27–1206, Revision 01, dated October 10, 2011. (ii) Reserved. (5) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 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. (6) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) 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/ibrlocations.html. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0113, dated June 15, 2016, 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–2017–0476. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–1405; fax 425–227–1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (p)(6) of this AD. jstallworth on DSKBBY8HB2PROD with RULES Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (o)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2014–08–01 are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 Section, Transport Standards Branch, 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. [Docket No. FAA–2017–0708; Product Identifier 2017–NM–035–AD; Amendment 39–19113; AD 2017–24–09] (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. VerDate Sep<11>2014 14:57 Nov 30, 2017 Jkt 244001 Issued in Renton, Washington, on November 16, 2017. Chris Spangenberg, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–25557 Filed 11–30–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2016–20– 11, which applied to certain Airbus Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Airbus Model A310 series airplanes. AD 2016–20–11 required repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 56865 beam, lock fitting, and torsion box plate, and repair if necessary. This new AD retains the inspections for cracking, and repair if necessary; and requires reinforcement of the aft cargo door sill beam area. This AD was prompted by the development of a reinforcement modification of the aft cargo door sill beam area, which constitutes terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 5, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 2, 2014 (79 FR 34403, June 17, 2014). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 3, 2017 (81 FR 85837, November 29, 2016). ADDRESSES: For service information identified in this final rule, 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. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 0708. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0708; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; E:\FR\FM\01DER1.SGM 01DER1

Agencies

[Federal Register Volume 82, Number 230 (Friday, December 1, 2017)]
[Rules and Regulations]
[Pages 56859-56865]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-25557]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / 
Rules and Regulations

[[Page 56859]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0476; Product Identifier 2016-NM-110-AD; Amendment 
39-19111; AD 2017-24-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-08-01, 
which applied to all Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2014-08-01 required an inspection for part numbers of the 
interconnecting struts and, for affected interconnecting struts, 
identification of the part and serial numbers of the associated target 
and proximity sensors and replacement or re-identification of the flap 
interconnecting strut if necessary. This AD continues to require an 
inspection to verify the interconnecting strut part number. This AD 
also provides a new compliance time and an additional inspection for 
previously inspected airplanes. This AD was prompted by an 
investigation that showed that when a certain combination of target/
proximity sensor serial numbers is installed on a flap interconnecting 
strut, a ``target FAR'' signal cannot be detected when reaching the 
mechanical end stop of the interconnecting strut. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective January 5, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 5, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of March 
26, 2014 (79 FR 9398, February 19, 2014).

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 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. You may view this referenced service information 
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0476.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0476; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, Washington 98057-3356; telephone 425-227-1405; fax 
425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-08-01, Amendment 39-17825 (79 FR 23900, 
April 29, 2014) (``AD 2014-08-01''). AD 2014-08-01 applied to all 
Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM 
published in the Federal Register on May 19, 2017 (82 FR 22918).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0113, dated June 15, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A318, A319, A320, and A321 series 
airplanes. The MCAI states:

    The flap interconnecting strut is a safety device of the High 
Lift System which acts as an alternative load path from one flap 
surface to another in case of a flap drive system disconnection. In 
such a failure case, the installed proximity sensors provide 
information to the slat flap control computer (SFCC) and the 
operation of the flap drive system is inhibited.
    An engineering investigation showed that, when a certain 
combination of target/sensor serial number (s/n) is installed on a 
flap interconnecting strut, a ``target FAR'' signal cannot be 
detected when reaching the mechanical end stop of the 
interconnecting strut.
    This condition, if not corrected, could cause a flap down drive 
disconnection to remain undetected, due to an already-failed 
interconnecting strut sensor, potentially resulting in asymmetric 
flap panel movement and consequent loss of control of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-27-1206 and SB A320-57-1164, to provide 
identification and replacement instructions for struts that have a 
certain target/sensor s/n combination installed. Aeroplanes on which 
modification (mod) 27956 had been accomplished in production were 
identified as not affected by the unsafe condition. Consequently, 
EASA issued [EASA] AD 2012-0012 [which corresponds to FAA AD 2014-
08-01] to require accomplishment of these inspections and corrective 
actions.
    Since that [EASA] AD was issued, Airbus has informed EASA about 
a batch of aeroplanes that were delivered with pre-mod 27956 Part 
Number (P/N) flap interconnecting strut(s) installed, but declared 
to be in post-mod configuration in the Aircraft Inspection Report. 
Airbus SB A320-57-1202 has been issued to provide instructions to 
verify the interconnecting strut P/N, and to update aircraft 
documentation.
    In addition, to ensure that all pre-mod parts are checked and 
corrected as required, SB A320-27-1206 was revised to include a 
wider range of P/N of affected interconnecting struts.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA

[[Page 56860]]

AD 2012-0012, which is superseded, expands the Applicability [adds 
affected part numbers], changes the compliance time and requires an 
additional inspection for aeroplanes that have already been 
inspected.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0476.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment. United Airlines and the Air Line 
Pilots Association, International supported the NPRM.

Request To Add Additional Identification Steps

    Delta Airlines (DAL) requested that additional identification steps 
be required in the NPRM to ensure that the affected parts are correctly 
identified. DAL stated that figure 1 to paragraphs (g) and (h) of the 
proposed AD contains part numbers for affected interconnecting struts. 
DAL commented that a review of its records from inspections conducted 
during compliance with AD 2014-08-01 determined that other part numbers 
were possible. DAL stated that it has had at least one instance of a 
part with the part number D5757032200000A.
    DAL stated that figure 2 to paragraphs (i)(2), (k), and (l) of the 
proposed AD adds the provision that additional alphanumeric characters 
may exist. DAL commented that while the NPRM removes some of the 
ambiguity that existed in AD 2014-08-01, a review of Airbus's Aircraft 
Illustrated Parts Catalog (AIPC) does not show any parts with a 
``letter'' suffix. DAL provided a photo that showed that the part 
number appears to ``wrap'' (to the next line) on the part. DAL stated 
that this ``wrapping'' condition has led to confusion in identifying 
the parts.
    DAL stated that per the Airbus AIPC Front Matter, the 13th, 14th, 
and 15th characters are controlled in specific ways. DAL also stated 
that the 13th and 14th characters are expected to be ``00'' and are 
used to fill out 12-digit base numbers on the part installed during 
production. DAL stated that the 15th character is a paint code 
designator and found the use of a paint code designator unusual on a 
part that is not viewable or expected to be painted to match an air 
carrier paint scheme. DAL commented that it believes the AD should be 
updated to show 00A, 00B, or the list of true possibilities, and the 
XXX allowance creates a significant number of possible part numbers 
that DAL must identify as prohibited.
    We agree to clarify the requirement to identify affected parts. 
Regarding the characters in the part number, identifying the last three 
characters are not required to identify a discrepant part; only the 
first twelve base numbers are required. Therefore, we do not agree to 
revise this AD to include a complete list of all possible combinations 
of these characters.
    We acknowledge the commenter's concern about the ``wrapping'' 
condition for part identification. However, in the photo provided by 
the commenter only the last three characters are ``wrapped.'' As stated 
previously, the last three characters are not required to identify a 
discrepant part.

Formatting Change to a Figure

    Figure 3 to paragraph (k)(1) of this AD has been reformatted to 
clarify affected manufacturer serial numbers.

Records Review

    We have determined that a review of maintenance records is 
acceptable for complying with the actions specified in paragraphs 
(i)(1) and (i)(2) of this AD, provided the part number of the installed 
interconnecting struts and the part number and the serial number of the 
associated target and proximity sensor can be conclusively determined 
from that review. We have revised paragraph (i) of this AD accordingly.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1206, Revision 02, dated 
November 2, 2015. The service information describes procedures for an 
inspection to determine the part number of the installed 
interconnecting struts and the part number and serial number of the 
associated target and proximity sensors, and procedures for replacement 
and re-identification of the interconnecting struts. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 1,032 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection and replacement           8 work-hours x $85 per hour              $0            $680        $701,760
 (retained actions from AD 2014-08-   = $680.
 01).
Inspection and replacement (new      15 work-hours x $85 per                   0           1,275       1,315,800
 action).                             hour = $1,275.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with

[[Page 56861]]

promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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) 
2014-08-01, Amendment 39-17825 (79 FR 23900, April 29, 2014), and 
adding the following new AD:

2017-24-07 Airbus: Amendment 39-19111; Docket No. FAA-2017-0476; 
Product Identifier 2016-NM-110-AD.

(a) Effective Date

    This AD is effective January 5, 2018.

(b) Affected ADs

    This AD replaces AD 2014-08-01, Amendment 39-17825 (79 FR 23900, 
April 29, 2014) (``AD 2014-08-01'').

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 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 an investigation that showed that when a 
certain combination of target/proximity sensor serial numbers is 
installed on a flap interconnecting strut, a ``target FAR'' signal 
cannot be detected when reaching the mechanical end stop of the 
interconnecting strut. We are issuing this AD to prevent an 
undetected flap down drive disconnection due to an already-failed 
interconnecting strut sensor, which could result in asymmetric flap 
panel movement and consequent loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Inspection To Determine the Part Number of the 
Interconnecting Struts, With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2014-08-01, with revised service information. Within 8,000 flight 
hours after March 26, 2014 (the effective date of AD 2014-03-08, 
Amendment 39-17745 (79 FR 9398, February 19, 2014) (``AD 2014-03-
08'')), inspect to determine the part number of the interconnecting 
struts installed on both the left-hand (LH) and right-hand (RH) 
wings of the airplane, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, Revision 01, 
dated October 10, 2011; or Airbus Service Bulletin A320-27-1206, 
Revision 02, dated November 2, 2015. A review of the airplane 
maintenance records is acceptable for determining the part number of 
the installed interconnecting struts, in lieu of the inspection, if 
the part number of the installed interconnecting struts, and the 
part number and the serial number of the associated target and 
proximity sensor, can be conclusively determined from that review. 
Accomplishment of the requirements of paragraph (i) of this AD 
terminates the requirements of this paragraph.
    (1) Airplanes on which Airbus Modification 27956 has been 
embodied in production, and on which no interconnecting strut has 
been replaced with a strut having a part number specified in figure 
1 to paragraphs (g) and (h) of this AD since the airplane's first 
flight: No further work is required by paragraph (g) of this AD.
    (2) If, during the inspection required by paragraph (g) of this 
AD, any interconnecting strut is installed with a part number 
specified in figure 1 to paragraphs (g) and (h) of this AD: Within 
8,000 flight hours after March 26, 2014 (the effective date of AD 
2014-03-08), determine the part number and the serial number of the 
associated target and proximity sensor.
    (i) For airplanes having conditions specified in paragraphs 
(g)(2)(i)(A), (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 
AD: Before further flight, replace the interconnecting strut with a 
serviceable unit, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-27-1206, Revision 01, dated October 
10, 2011; or Airbus Service Bulletin A320-27-1206, Revision 02, 
dated November 2, 2015. For the purposes of paragraph (g) of this 
AD, a serviceable interconnecting strut is a unit that has been 
determined to be in compliance with the requirements of paragraph 
(g) of this AD.
    (A) A target part number (P/N) ABS0121-13 or P/N 8-536-01; and
    (B) A target serial number lower than 1600, or a target serial 
number that is unreadable; and
    (C) A proximity sensor having P/N ABS0121-31 or P/N 8-372-04; 
and
    (D) A proximity sensor having a serial number between C59198 and 
C59435, or a serial number (S/N) C500000 or higher.
    (ii) For a target having S/N 1600 or higher and target P/N 
ABS0121-13 or P/N 8-536-01: Within 8,000 flight hours after March 
26, 2014 (the effective date of AD 2014-03-08), re-identify the 
interconnecting strut, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, Revision 01, 
dated October 10, 2011; or Airbus Service Bulletin A320-27-1206, 
Revision 02, dated November 2, 2015.
BILLING CODE 4910-13-P

[[Page 56862]]

[GRAPHIC] [TIFF OMITTED] TR01DE17.000

(h) Retained Parts Installation Prohibition, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2014-08-01, with no changes. As of March 26, 2014 (the effective 
date of AD 2014-03-08), no person may install an interconnecting 
strut with a part number specified in figure 1 to paragraphs (g) and 
(h) of this AD, on any airplane, except for parts identified in 
paragraph (g)(2)(ii) of this AD, provided that the actions in 
paragraph (g)(2)(ii) are done. As of the effective date of this AD, 
comply with the requirements of paragraph (l) of this AD in lieu of 
the requirements of this paragraph.

(i) New Requirements of This AD: Inspection To Determine the Part 
Number of the Interconnecting Struts and the Part Number and Serial 
Number of the Associated Target and Proximity Sensor

    Within 24 months after the effective date of this AD, accomplish 
the actions specified in paragraphs (i)(1) and (i)(2) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1206, Revision 02, dated November 2, 2015. 
Accomplishment of the actions specified in this paragraph terminates 
the requirements of paragraph (g) of this AD. In lieu of doing the 
actions specified in paragraphs (i)(1) and (i)(2) of this AD, a 
review of the airplane maintenance records is acceptable for 
determining the part number of the installed interconnecting struts 
and the part number and the serial number of the associated target 
and proximity sensor, if the part number and serial numbers can be 
conclusively determined from that review.
    (1) Inspect to determine the part number of the interconnecting 
struts installed on both the LH and RH wings on the airplane.
    (2) If an interconnecting strut is installed with a part number 
specified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, 
identify the part number and the serial number of the associated 
target and proximity sensor; and for the target and proximity sensor 
part number and serial number combination specified in paragraph (j) 
of this AD, within the compliance times specified in paragraph (j) 
of this AD, do the actions specified in paragraph (j) of this AD for 
that interconnecting strut.

[[Page 56863]]

[GRAPHIC] [TIFF OMITTED] TR01DE17.001

(j) New Requirements of This AD: Replacement or Re-Identification

    (1) If the target serial number is lower than 1600 or is 
unreadable, and the proximity sensor part number is P/N ABS0121-31 
or P/N 8-372-04 with a serial number between S/N C59198 and C59435, 
or S/N C500000 or higher: Before further flight, do the actions 
specified by paragraph (j)(1)(i) or (j)(1)(ii) of this AD. For the 
purposes of paragraph (j) of this AD, a serviceable interconnecting 
strut is a unit that has been determined to be in compliance with 
the requirements of paragraphs (i) and (j) of this AD.
    (i) Replace the interconnecting strut with a serviceable unit, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
    (ii) Do a general visual inspection of the flap down drive to 
detect discrepancies, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, Revision 02, 
dated November 2, 2015.
    (A) If no discrepancy is found, within 50 flight cycles after 
the inspection, replace the interconnecting strut with a serviceable 
unit, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
    (B) If any discrepancy is found, before further flight, replace 
the interconnecting strut with a serviceable unit, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-27-1206, Revision 02, dated November 2, 2015.
    (2) If the target serial number is 1600 or higher (with any 
proximity sensor part number and serial number): Within 24 months 
after the effective date of this AD, re-identify the interconnecting 
strut, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-27-1206, Revision 02, dated November 2, 2015.

(k) Additional Provisions of This AD

    (1) Airplanes on which Airbus Modification 27956 has been 
embodied in production, and on which no interconnecting strut with a 
part number identified in figure 2 to paragraphs (i)(2), (k), and 
(l) of this AD has been installed since the airplane's first flight, 
are not affected by the requirements of paragraph (i) of this AD, 
except for those manufacturer serial numbers specified in figure 3 
to paragraph (k)(1) of this AD. Airplanes having manufacturer serial 
numbers specified in figure 3 to paragraph (k)(1) of this AD are 
affected by the requirements of paragraph (i) of this AD.
    (2) For an airplane that has already been inspected before the 
effective date of this AD as specified in the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, dated January 
28, 2011; or Revision 01, dated October 10, 2011: Within the 
compliance time specified in paragraph (i) of this AD, accomplish 
the additional work specified in and in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1206, 
Revision 02, dated November 2, 2015, unless it is determined that no 
interconnecting strut with a part number specified in figure 2 to 
paragraphs (i)(2), (k), and (l) of this AD is installed on that 
airplane. A review of airplane maintenance records is acceptable to 
make this determination, provided the part number can be 
conclusively identified from that review.

[[Page 56864]]

[GRAPHIC] [TIFF OMITTED] TR01DE17.002

BILLING CODE 4910-13-C

(l) New Requirement of This AD: Parts Installation Limitations

    As of the effective date of this AD, no person may install, on 
any airplane, an interconnecting strut with a part number specified 
in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, unless it 
is in compliance with the requirements of this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before 
March 26, 2014 (the effective date of AD 2014-03-08), using Airbus 
Service Bulletin A320-27-1206, dated January 28, 2011, and if 
additional work since March 26, 2014 (the effective date of AD 2014-
03-08) has been accomplished using Airbus Service Bulletin A320-27-
1206, Revision 01, dated October 10, 2011.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International

[[Page 56865]]

Section, Transport Standards Branch, 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 Section, send it to the attention of the person 
identified in paragraph (o)(2) of this AD. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 2014-08-01 are approved as 
AMOCs for the corresponding provisions of paragraphs (g) and (h) of 
this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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 Section, Transport Standards 
Branch, 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

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0113, dated June 15, 2016, 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-2017-0476.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; 
telephone 425-227-1405; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (p)(6) of this AD.

(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.
    (3) The following service information was approved for IBR on 
January 5, 2018.
    (i) Airbus Service Bulletin A320-27-1206, Revision 02, dated 
November 2, 2015.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
March 26, 2014 (79 FR 9398, February 19, 2014).
    (i) Airbus Service Bulletin A320-27-1206, Revision 01, dated 
October 10, 2011.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 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.
    (6) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (7) 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.

    Issued in Renton, Washington, on November 16, 2017.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-25557 Filed 11-30-17; 8:45 am]
BILLING CODE 4910-13-P