82 FR 22918 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 96 (May 19, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 96 (May 19, 2017)
| Page Range | 22918-22922 | |
| FR Document | 2017-10134 |
[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)] [Proposed Rules] [Pages 22918-22922] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10134] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0476; Directorate Identifier 2016-NM-110-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-08- 01, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-08-01 currently requires 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. Since we issued AD 2014-08-01, we have determined that certain airplanes must be inspected to verify the interconnecting strut part number. This proposed AD would add airplanes to the applicability. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 [email protected]; Internet http://www.airbus.com. You may view this referenced 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. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227- 1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0476; Directorate Identifier 2016-NM-110-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. [[Page 22919]] Discussion On April 7, 2014, we issued AD 2014-08-01, Amendment 39-17825 (79 FR 23900, April 29, 2014) (``AD 2014-08-01''), for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-08-01 superseded AD 2014-03-08, Amendment 39-17745 (79 FR 9398, February 19, 2014) (``AD 2014-03-08''). AD 2014-08-01 was prompted by a report that an investigation 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 it reaches the mechanical end stop of the interconnecting strut. AD 2014-08-01 requires an inspection to determine the part number of the interconnecting struts installed on the wings, identifying the part number and the serial number of the associated target and proximity sensor if applicable, and replacing or re-identifying the flap interconnecting strut if applicable. We issued AD 2014-08-01 to correct the definition of a serviceable interconnecting strut. Since we issued AD 2014-08-01, we received a report that airplanes were delivered with pre-modification 27956 part number installed on the flap interconnecting strut(s), but declared to be in post-modification configuration in the Aircraft Inspection Report. We have determined that certain airplanes must be inspected to verify the interconnecting strut part number. 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- 03-08] 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 AD 2012-0012, which is superseded, expands the Applicability, 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. 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 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 sensor, and 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 1,032 airplanes of U.S. registry. The actions required by AD 2014-08-01, and retained in this proposed AD, take about 8 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2014-08-01 is $680 per product. We also estimate that it would take about 15 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $1,315,800, or $1,275 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed 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 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. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 [[Page 22920]] responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: Airbus: Docket No. FAA-2017-0476; Directorate Identifier 2016-NM- 110-AD. (a) Comments Due Date We must receive comments by July 3, 2017. (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 a report that an investigation showed that when a certain combination of a 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 detect and correct a latent failure of the 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 which 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. Figure 1 to Paragraphs (g) and (h) of This AD--Interconnecting Strut Part Numbers ------------------------------------------------------------------------ Interconnecting strut part numbers ------------------------------------------------------------------------- D5757030500000 D5757030500100 D5757030500200 D5757030500600 D5757030500800 D5757030501000 D5757030501200 D5757032200000 ------------------------------------------------------------------------ (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 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. (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 [[Page 22921]] 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. Figure 2 to Paragraphs (i)(2), (k), and (l) of This AD--Affected Interconnecting Struts [XXX signifies any alpha-numeric combination. It may be possible to find units with only XX] ------------------------------------------------------------------------- D57570305000XXX D57570305001XXX D57570305002XXX D57570305006XXX D57570305008XXX D57570305010XXX D57570305012XXX D57570322000XXX ------------------------------------------------------------------------ (j) New Requirements of This AD: Replacement or Reidentification (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 required 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 which 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 is 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 1, 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 2, 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. Figure 3 to Paragraph (k)(1) of This AD--Additional Affected Manufacturer Serial Numbers ---------------------------------------------------------------------------------------------------------------- Airplane model-- Affected Manufacturer Serial Numbers-- ---------------------------------------------------------------------------------------------------------------- A320 series airplanes........................... 1857 1858 1860 1861 1864 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 A319 series airplanes........................... 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 ---------------------------------------------------------------------------------------------------------------- (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 has been modified in accordance 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- [[Page 22922]] 08), using Airbus Service Bulletin A320-27-1206, dated January 28, 2011, and if additional work 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 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: [email protected]. (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 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 (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 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 [email protected]; Internet http://www.airbus.com. 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. Issued in Renton, Washington, on May 11, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10134 Filed 5-18-17; 8:45 am] BILLING CODE 4910-13-P
![22918 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
(2) Where Boeing Alert Service Bulletin MC 110–SK57, Seal Beach, CA 90740–5600; • Hand Delivery: Deliver to Mail
757–53A0101, dated November 8, 2016, telephone 562–797–1717; Internet https:// address above between 9 a.m. and 5
specifies to contact Boeing for appropriate www.myboeingfleet.com. You may view this p.m., Monday through Friday, except
action and identifies that action as ‘‘RC’’ referenced service information at the FAA, Federal holidays.
(Required for Compliance): Before further Transport Airplane Directorate, 1601 Lind
flight, repair the crack using a method Avenue SW., Renton, WA. For information For service information identified in
approved in accordance with the procedures on the availability of this material at the this NPRM, contact Airbus,
specified in paragraph (j) of this AD. FAA, call 425–227–1221. Airworthiness Office—EIAS, 1 Rond
(j) Alternative Methods of Compliance Issued in Renton, Washington, on May 10, Point Maurice Bellonte, 31707 Blagnac
(AMOCs) 2017. Cedex, France; telephone +33 5 61 93 36
Michael Kaszycki, 96; fax +33 5 61 93 44 51; email
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the Acting Manager, Transport Airplane
account.airworth-eas@airbus.com;
authority to approve AMOCs for this AD, if Directorate, Aircraft Certification Service. Internet http://www.airbus.com. You
requested using the procedures found in 14 [FR Doc. 2017–10033 Filed 5–18–17; 8:45 am]
may view this referenced service
CFR 39.19. In accordance with 14 CFR 39.19, information at the FAA, Transport
BILLING CODE 4910–13–P
send your request to your principal inspector Airplane Directorate, 1601 Lind Avenue
or local Flight Standards District Office, as SW., Renton, WA. For information on
appropriate. If sending information directly the availability of this material at the
to the manager of the ACO, send it to the DEPARTMENT OF TRANSPORTATION
FAA, call 425–227–1221.
attention of the person identified in
paragraph (k)(1) of this AD. Information may Federal Aviation Administration Examining the AD Docket
be emailed to: 9-ANM-LAACO-AMOC-
Requests@faa.gov. 14 CFR Part 39 You may examine the AD docket on
(2) Before using any approved AMOC, the Internet at http://
[Docket No. FAA–2017–0476; Directorate
notify your appropriate principal inspector, Identifier 2016–NM–110–AD]
www.regulations.gov by searching for
or lacking a principal inspector, the manager and locating Docket No. FAA–2017–
of the local flight standards district office/ RIN 2120–AA64 0476; or in person at the Docket
certificate holding district office. Management Facility between 9 a.m.
(3) An AMOC that provides an acceptable Airworthiness Directives; Airbus and 5 p.m., Monday through Friday,
level of safety may be used for any repair, Airplanes except Federal holidays. The AD docket
modification, or alteration required by this
AD if it is approved by the Boeing AGENCY: Federal Aviation contains this proposed AD, the
Commercial Airplanes Organization Administration (FAA), DOT. regulatory evaluation, any comments
Designation Authorization (ODA) that has ACTION: Notice of proposed rulemaking received, and other information. The
been authorized by the Manager, Los Angeles (NPRM). street address for the Docket Operations
ACO, to make those findings. To be office (telephone 800–647–5527) is in
approved, the repair method, modification We propose to supersede
SUMMARY: the ADDRESSES section. Comments will
deviation, or alteration deviation must meetAirworthiness Directive (AD) 2014–08– be available in the AD docket shortly
the certification basis of the airplane, and the
01, for all Airbus Model A318, A319, after receipt.
approval must specifically refer to this AD.A320, and A321 series airplanes. AD
(4) Except as required by paragraph (i)(2) FOR FURTHER INFORMATION CONTACT:
of this AD: For service information that
2014–08–01 currently requires an Sanjay Ralhan, Aerospace Engineer,
contains steps that are labeled as RC, the inspection for part numbers of the International Branch, ANM–116,
interconnecting struts and, for affected
provisions of paragraphs (j)(4)(i) and (j)(4)(ii) Transport Airplane Directorate, FAA,
of this AD apply. interconnecting struts, identification of 1601 Lind Avenue SW., Renton,
(i) The steps labeled as RC, including the part and serial numbers of the Washington 98057–3356; telephone
substeps under an RC step and any figures associated target and proximity sensors
identified in an RC step, must be done to 425–227–1405; fax 425–227–1149.
and replacement or re-identification of
comply with the AD. If a step or substep is the flap interconnecting strut if SUPPLEMENTARY INFORMATION:
labeled ‘‘RC Exempt,’’ then the RC necessary. Since we issued AD 2014–
requirement is removed from that step or Comments Invited
substep. An AMOC is required for any
08–01, we have determined that certain
airplanes must be inspected to verify the We invite you to send any written
deviations to RC steps, including substeps
and identified figures. interconnecting strut part number. This relevant data, views, or arguments about
(ii) Steps not labeled as RC may be proposed AD would add airplanes to the this proposed AD. Send your comments
deviated from using accepted methods in applicability. We are proposing this AD to an address listed under the
accordance with the operator’s maintenance to address the unsafe condition on these ADDRESSES section. Include ‘‘Docket No.
or inspection program without obtaining products. FAA–2017–0476; Directorate Identifier
approval of an AMOC, provided the RC steps, 2016–NM–110–AD’’ at the beginning of
DATES: We must receive comments on
including substeps and identified figures, can your comments. We specifically invite
still be done as specified, and the airplanethis proposed AD by July 3, 2017.
ADDRESSES: You may send comments,
comments on the overall regulatory,
can be put back in an airworthy condition.
using the procedures found in 14 CFR economic, environmental, and energy
(k) Related Information
11.43 and 11.45, by any of the following aspects of this proposed AD. We will
(1) For more information about this AD, methods: consider all comments received by the
contact Muoi Vuong, Aerospace Engineer, • Federal eRulemaking Portal: Go to closing date and may amend this
sradovich on DSK3GMQ082PROD with PROPOSALS
Airframe Branch, ANM–120L, FAA, Los http://www.regulations.gov. Follow the proposed AD based on those comments.
Angeles ACO, 3960 Paramount Boulevard, We will post all comments we
Lakewood, CA 90712–4137; phone: 562–627–
instructions for submitting comments.
5205; fax: 562–627–5210; email:
• Fax: 202–493–2251. receive, without change, to http://
Muoi.Vuong@faa.gov.
• Mail: U.S. Department of www.regulations.gov, including any
(2) For service information identified in Transportation, Docket Operations, M– personal information you provide. We
this AD, contact Boeing Commercial 30, West Building Ground Floor, Room will also post a report summarizing each
Airplanes, Attention: Contractual & Data W12–140, 1200 New Jersey Avenue SE., substantive verbal contact we receive
Services (C&DS), 2600 Westminster Blvd., Washington, DC 20590. about this proposed AD.
VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\19MYP1.SGM 19MYP1](https://thefederalregister.org/doc/82_FR_23014/page/1.svg)
![Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules 22919
Discussion and consequent loss of control of the referenced above. We are proposing this
aeroplane. AD because we evaluated all pertinent
On April 7, 2014, we issued AD 2014– To address this potential unsafe condition,
08–01, Amendment 39–17825 (79 FR information and determined an unsafe
Airbus issued Service Bulletin (SB) A320–
23900, April 29, 2014) (‘‘AD 2014–08– condition exists and is likely to exist or
27–1206 and SB A320–57–1164, to provide
01’’), for all Airbus Model A318, A319, identification and replacement instructions develop on other products of these same
A320, and A321 series airplanes. AD for struts that have a certain target/sensor type designs.
2014–08–01 superseded AD 2014–03– s/n combination installed. Aeroplanes on Costs of Compliance
08, Amendment 39–17745 (79 FR 9398, which modification (mod) 27956 had been
February 19, 2014) (‘‘AD 2014–03–08’’). accomplished in production were identified We estimate that this proposed AD
as not affected by the unsafe condition. affects 1,032 airplanes of U.S. registry.
AD 2014–08–01 was prompted by a
Consequently, EASA issued [EASA] AD The actions required by AD 2014–08–
report that an investigation showed that 2012–0012 [which corresponds to FAA AD
when a certain combination of target/ 01, and retained in this proposed AD,
2014–03–08] to require accomplishment of
proximity sensor serial numbers is these inspections and corrective actions.
take about 8 work-hours per product, at
installed on a flap interconnecting strut, Since that [EASA] AD was issued, Airbus an average labor rate of $85 per work-
a ‘‘target FAR’’ signal cannot be detected has informed EASA about a batch of hour. Required parts cost about $0 per
when it reaches the mechanical end aeroplanes that were delivered with pre-mod product. Based on these figures, the
stop of the interconnecting strut. AD 27956 Part Number (P/N) flap estimated cost of the actions that are
2014–08–01 requires an inspection to interconnecting strut(s) installed, but required by AD 2014–08–01 is $680 per
declared to be in post-mod configuration in product.
determine the part number of the
the Aircraft Inspection Report. Airbus SB We also estimate that it would take
interconnecting struts installed on the A320–57–1202 has been issued to provide
wings, identifying the part number and about 15 work-hours per product to
instructions to verify the interconnecting
the serial number of the associated strut P/N, and to update aircraft comply with the basic requirements of
target and proximity sensor if documentation. this proposed AD. The average labor
applicable, and replacing or re- In addition, to ensure that all pre-mod rate is $85 per work-hour. Required
identifying the flap interconnecting parts are checked and corrected as required, parts would cost about $0 per product.
strut if applicable. We issued AD 2014– SB A320–27–1206 was revised to include a Based on these figures, we estimate the
08–01 to correct the definition of a wider range of P/N of affected cost of this proposed AD on U.S.
interconnecting struts. operators to be $1,315,800, or $1,275 per
serviceable interconnecting strut.
For the reasons described above, this product.
Since we issued AD 2014–08–01, we
[EASA] AD retains the requirements of EASA
received a report that airplanes were AD 2012–0012, which is superseded,
We have received no definitive data
delivered with pre-modification 27956 expands the Applicability, changes the that would enable us to provide cost
part number installed on the flap compliance time and requires an additional estimates for the on-condition actions
interconnecting strut(s), but declared to inspection for aeroplanes that have already specified in this proposed AD.
be in post-modification configuration in been inspected.
Authority for This Rulemaking
the Aircraft Inspection Report. We have You may examine the MCAI in the
determined that certain airplanes must AD docket on the Internet at http:// Title 49 of the United States Code
be inspected to verify the www.regulations.gov by searching for specifies the FAA’s authority to issue
interconnecting strut part number. and locating Docket No. FAA–2017– rules on aviation safety. Subtitle I,
The European Aviation Safety Agency 0476. section 106, describes the authority of
(EASA), which is the Technical Agent the FAA Administrator. ‘‘Subtitle VII:
for the Member States of the European Related Service Information Under 1 Aviation Programs,’’ describes in more
Union, has issued EASA AD 2016–0113, CFR Part 51 detail the scope of the Agency’s
dated June 15, 2016 (referred to after Airbus has issued Service Bulletin authority.
this as the Mandatory Continuing A320–27–1206, Revision 02, dated We are issuing this rulemaking under
Airworthiness Information, or ‘‘the November 2, 2015. The service the authority described in ‘‘Subtitle VII,
MCAI’’), to correct an unsafe condition information describes an inspection to Part A, Subpart III, Section 44701:
for all Airbus Model A318, A319, A320, determine the part number of the General requirements.’’ Under that
and A321 series airplanes. The MCAI installed interconnecting struts and the section, Congress charges the FAA with
states: part number and serial number of the promoting safe flight of civil aircraft in
The flap interconnecting strut is a safety associated target and proximity sensor, air commerce by prescribing regulations
device of the High Lift System which acts as and replacement and re-identification of for practices, methods, and procedures
an alternative load path from one flap surface the interconnecting struts. This service the Administrator finds necessary for
to another in case of a flap drive system information is reasonably available safety in air commerce. This regulation
disconnection. In such a failure case, the because the interested parties have is within the scope of that authority
installed proximity sensors provide because it addresses an unsafe condition
information to the slat flap control computer access to it through their normal course
(SFCC) and the operation of the flap drive of business or by the means identified that is likely to exist or develop on
system is inhibited. in the ADDRESSES section. products identified in this rulemaking
An engineering investigation showed that, action.
when a certain combination of target/sensor
FAA’s Determination and Requirements
of This Proposed AD Regulatory Findings
serial number (s/n) is installed on a flap
sradovich on DSK3GMQ082PROD with PROPOSALS
interconnecting strut, a ‘‘target FAR’’ signal This product has been approved by We determined that this proposed AD
cannot be detected when reaching the the aviation authority of another would not have federalism implications
mechanical end stop of the interconnecting country, and is approved for operation under Executive Order 13132. This
strut.
This condition, if not corrected, could
in the United States. Pursuant to our proposed AD would not have a
cause a flap down drive disconnection to bilateral agreement with the State of substantial direct effect on the States, on
remain undetected, due to an already-failed Design Authority, we have been notified the relationship between the national
interconnecting strut sensor, potentially of the unsafe condition described in the Government and the States, or on the
resulting in asymmetric flap panel movement MCAI and service information distribution of power and
VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 E:\FR\FM\19MYP1.SGM 19MYP1](https://thefederalregister.org/doc/82_FR_23014/page/2.svg)
![22920 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
responsibilities among the various interconnecting strut, a ‘‘target FAR’’ signal compliance with the requirements of
levels of government. cannot be detected when reaching the paragraph (g) of this AD.
For the reasons discussed above, I mechanical end stop of the interconnecting (A) A target part number (P/N) ABS0121–
strut. We are issuing this AD to detect and 13 or P/N 8–536–01; and
certify this proposed regulation:
correct a latent failure of the flap down drive (B) A target serial number lower than 1600,
1. Is not a ‘‘significant regulatory disconnection due to an already-failed or a target serial number that is unreadable;
action’’ under Executive Order 12866; interconnecting strut sensor, which could and
2. Is not a ‘‘significant rule’’ under the result in asymmetric flap panel movement (C) A proximity sensor having P/N
DOT Regulatory Policies and Procedures and consequent loss of control of the ABS0121–31 or P/N 8–372–04; and
(44 FR 11034, February 26, 1979); airplane. (D) A proximity sensor having a serial
3. Will not affect intrastate aviation in number between C59198 and C59435, or a
(f) Compliance serial number (S/N) C500000 or higher.
Alaska; and
4. Will not have a significant Comply with this AD within the (ii) For a target having S/N 1600 or higher
compliance times specified, unless already and target P/N ABS0121–13 or P/N 8–536–
economic impact, positive or negative, 01: Within 8,000 flight hours after March 26,
done.
on a substantial number of small entities 2014 (the effective date of AD 2014–03–08),
under the criteria of the Regulatory (g) Retained Inspection to Determine the Part re-identify the interconnecting strut, in
Flexibility Act. Number of the Interconnecting Struts, With accordance with the Accomplishment
Revised Service Information Instructions of Airbus Service Bulletin A320–
List of Subjects in 14 CFR Part 39 This paragraph restates the requirements of 27–1206, Revision 01, dated October 10,
Air transportation, Aircraft, Aviation paragraph (g) of AD 2014–08–01, with 2011; or Airbus Service Bulletin A320–27–
safety, Incorporation by reference, revised service information. Within 8,000 1206, Revision 02, dated November 2, 2015.
Safety. flight hours after March 26, 2014 (the
effective date of AD 2014–03–08, FIGURE 1 TO PARAGRAPHS (g) AND (h)
The Proposed Amendment Amendment 39–17745 (79 FR 9398, February OF THIS AD—INTERCONNECTING
19, 2014) (‘‘AD 2014–03–08’’)), inspect to
Accordingly, under the authority determine the part number of the STRUT PART NUMBERS
delegated to me by the Administrator, interconnecting struts installed on both the
the FAA proposes to amend 14 CFR part left-hand (LH) and right-hand (RH) wings of Interconnecting strut part numbers
39 as follows: the airplane, in accordance with the
Accomplishment Instructions of Airbus D5757030500000
PART 39—AIRWORTHINESS Service Bulletin A320–27–1206, Revision 01, D5757030500100
DIRECTIVES dated October 10, 2011; or Airbus Service D5757030500200
Bulletin A320–27–1206, Revision 02, dated D5757030500600
■ 1. The authority citation for part 39 November 2, 2015. A review of the airplane D5757030500800
maintenance records is acceptable for D5757030501000
continues to read as follows: D5757030501200
determining the part number of the installed
Authority: 49 U.S.C. 106(g), 40113, 44701. interconnecting struts, in lieu of the D5757032200000
§ 39.13 [Amended] inspection, if the part number of the installed
interconnecting struts, and the part number (h) Retained Parts Installation Prohibition,
■ 2. The FAA amends § 39.13 by and the serial number of the associated target With No Changes
removing Airworthiness Directive (AD) and proximity sensor, can be conclusively This paragraph restates the requirements of
2014–08–01, Amendment 39–17825 (79 determined from that review. paragraph (h) of AD 2014–08–01, with no
FR 23900, April 29, 2014), and adding Accomplishment of the requirements of changes. As of March 26, 2014 (the effective
the following new AD: paragraph (i) of this AD terminates the date of AD 2014–03–08), no person may
requirements of this paragraph. install an interconnecting strut with a part
Airbus: Docket No. FAA–2017–0476;
(1) Airplanes on which Airbus number specified in figure 1 to paragraphs (g)
Directorate Identifier 2016–NM–110–AD.
Modification 27956 has been embodied in and (h) of this AD, on any airplane, except
(a) Comments Due Date production, and on which no interconnecting for parts identified in paragraph (g)(2)(ii) of
We must receive comments by July 3, 2017. strut has been replaced with a strut having this AD, provided that the actions in
a part number specified in figure 1 to paragraph (g)(2)(ii) are done. As of the
(b) Affected ADs paragraphs (g) and (h) of this AD since the effective date of this AD, comply with the
This AD replaces AD 2014–08–01, airplane’s first flight: No further work is requirements of paragraph (l) of this AD in
Amendment 39–17825 (79 FR 23900, April required by paragraph (g) of this AD. lieu of the requirements of this paragraph.
29, 2014) (‘‘AD 2014–08–01’’). (2) If, during the inspection required by
paragraph (g) of this AD, any interconnecting (i) New Requirements of This AD: Inspection
(c) Applicability strut is installed with a part number specified To Determine the Part Number of the
in figure 1 to paragraphs (g) and (h) of this Interconnecting Struts and the Associated
This AD applies to Airbus Model A318– Target and Proximity Sensor
111, –112, –121, and –122 airplanes; Model AD: Within 8,000 flight hours after March 26,
A319–111, –112, –113, –114, –115, –131, 2014 (the effective date of AD 2014–03–08), Within 24 months after the effective date
–132, and –133 airplanes; Model A320–211, determine the part number and the serial of this AD, accomplish the actions specified
–212, –214, –231, –232, and –233 airplanes; number of the associated target and in paragraphs (i)(1) and (i)(2) of this AD, in
and Model A321–111, –112, –131, –211, proximity sensor. accordance with the Accomplishment
–212, –213, –231, and –232 airplanes; (i) For airplanes having conditions Instructions of Airbus Service Bulletin A320–
certificated in any category; all manufacturer specified in paragraphs (g)(2)(i)(A), 27–1206, Revision 02, dated November 2,
serial numbers. (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 2015. Accomplishment of the actions
AD: Before further flight, replace the specified in this paragraph terminates the
sradovich on DSK3GMQ082PROD with PROPOSALS
(d) Subject interconnecting strut with a serviceable unit, requirements of paragraph (g) of this AD.
Air Transport Association (ATA) of in accordance with the Accomplishment (1) Inspect to determine the part number of
America Code 27, Flight controls. Instructions of Airbus Service Bulletin A320– the interconnecting struts installed on both
27–1206, Revision 01, dated October 10, the LH and RH wings on the airplane.
(e) Reason 2011; or Airbus Service Bulletin A320–27– (2) If an interconnecting strut is installed
This AD was prompted by a report that an 1206, Revision 02, dated November 2, 2015. with a part number specified in figure 2 to
investigation showed that when a certain For the purposes of paragraph (g) of this AD, paragraphs (i)(2), (k), and (l) of this AD,
combination of a target/proximity sensor a serviceable interconnecting strut is a unit identify the part number and the serial
serial numbers is installed on a flap which has been determined to be in number of the associated target and
VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\19MYP1.SGM 19MYP1](https://thefederalregister.org/doc/82_FR_23014/page/3.svg)
![Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules 22921
proximity sensor; and for the target and compliance with the requirements of (k) Additional Provisions of This AD
proximity sensor part number and serial paragraphs (i) and (j) of this AD. (1) Airplanes on which Airbus
number combination specified in paragraph (i) Replace the interconnecting strut with a Modification 27956 has been embodied in
(j) of this AD, within the compliance times serviceable unit, in accordance with the production, and on which no interconnecting
specified in paragraph (j) of this AD, do the Accomplishment Instructions of Airbus strut with a part number identified in figure
actions specified in paragraph (j) of this AD Service Bulletin A320–27–1206, Revision 02, 2 to paragraphs (i)(2), (k), and (l) of this AD
for that interconnecting strut. dated November 2, 2015. is installed since the airplane’s first flight, are
(ii) Do a general visual inspection of the not affected by the requirements of paragraph
FIGURE 2 TO PARAGRAPHS (i)(2), (k), flap down drive to detect discrepancies, in (i) of this AD, except for those manufacturer
AND (l) OF THIS AD—AFFECTED accordance with the Accomplishment serial numbers specified in figure 3 to
Instructions of Airbus Service Bulletin A320– paragraph (k)(1) of this AD. Airplanes having
INTERCONNECTING STRUTS 27–1206, Revision 02, dated November 2, manufacturer serial numbers specified in
[XXX signifies any alpha-numeric combination. 2015.
It may be possible to find units with only XX] figure 3 to paragraph (k)(1) of this AD are
(A) If no discrepancy is found, within 50 affected by the requirements of paragraph (i)
flight cycles after the inspection, replace the of this AD.
D57570305000XXX
D57570305001XXX
interconnecting strut with a serviceable unit, (2) For an airplane that has already been
D57570305002XXX in accordance with the Accomplishment inspected before the effective date of this AD
D57570305006XXX Instructions of Airbus Service Bulletin A320– as specified in the Accomplishment
D57570305008XXX 27–1206, Revision 02, dated November 2, Instructions of Airbus Service Bulletin A320–
D57570305010XXX 2015. 27–1206, dated January 28, 2011; or Revision
D57570305012XXX (B) If any discrepancy is found, before 1, dated October 10, 2011: Within the
D57570322000XXX further flight, replace the interconnecting compliance time specified in paragraph (i) of
strut with a serviceable unit, in accordance this AD, accomplish the additional work
(j) New Requirements of This AD: with the Accomplishment Instructions of specified in and in accordance with the
Replacement or Reidentification Airbus Service Bulletin A320–27–1206, Accomplishment Instructions of Airbus
(1) If the target serial number is lower than Revision 02, dated November 2, 2015. Service Bulletin A320–27–1206, Revision 2,
1600 or is unreadable, and the proximity (2) If the target serial number is 1600 or dated November 2, 2015, unless it is
sensor part number is P/N ABS0121–31 or P/ higher (with any proximity sensor part determined that no interconnecting strut
N 8–372–04 with a serial number between S/ number and serial number): Within 24 with a part number specified in figure 2 to
N C59198 and C59435, or S/N C500000 or months after the effective date of this AD, re- paragraphs (i)(2), (k), and (l) of this AD is
higher: Before further flight, do the actions identify the interconnecting strut, in installed on that airplane. A review of
required by paragraph (j)(1)(i) or (j)(1)(ii) of accordance with the Accomplishment airplane maintenance records is acceptable to
this AD. For the purposes of paragraph (j) of Instructions of Airbus Service Bulletin A320– make this determination, provided the part
this AD, a serviceable interconnecting strut is 27–1206, Revision 02, dated November 2, number can be conclusively identified from
a unit which has been determined to be in 2015. that review.
FIGURE 3 TO PARAGRAPH (k)(1) OF THIS AD—ADDITIONAL AFFECTED MANUFACTURER SERIAL NUMBERS
Airplane model— Affected Manufacturer Serial Numbers—
A320 series airplanes ...................................................................................... 1857 1858 1860 1861
1864 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
A319 series airplanes ...................................................................................... 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
sradovich on DSK3GMQ082PROD with PROPOSALS
1943 1947
(l) New Requirement of This AD: Parts specified in figure 2 to paragraphs (i)(2), (k), (m) Credit for Previous Actions
Installation Limitations and (l) of this AD, unless it has been This paragraph provides credit for the
As of the effective date of this AD, no modified in accordance with the actions required by paragraph (g) of this AD,
person may install, on any airplane, an requirements of this AD. if those actions were performed before March
interconnecting strut with a part number 26, 2014 (the effective date of AD 2014–03–
VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\19MYP1.SGM 19MYP1](https://thefederalregister.org/doc/82_FR_23014/page/4.svg)
![22922 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
08), using Airbus Service Bulletin A320–27– Bellonte, 31707 Blagnac Cedex, France; comments through the Internet at http://
1206, dated January 28, 2011, and if telephone +33 5 61 93 36 96; fax +33 5 61 www.regulations.gov. You may review
additional work has been accomplished 93 44 51; email account.airworth-eas@ the public docket containing the
using Airbus Service Bulletin A320–27–1206, airbus.com; Internet http://www.airbus.com. proposal, any comments received, and
Revision 01, dated October 10, 2011. You may view this service information at the
FAA, Transport Airplane Directorate, 1601
any final disposition in person in the
(n) Other FAA AD Provisions
Lind Avenue SW., Renton, WA. For Dockets Office between 9:00 a.m. and
The following provisions also apply to this information on the availability of this 5:00 p.m., Monday through Friday,
AD: material at the FAA, call 425–227–1221. except federal holidays.
(1) Alternative Methods of Compliance FAA Order 7400.11A, Airspace
Issued in Renton, Washington, on May 11,
(AMOCs): The Manager, International Designations and Reporting Points, and
Branch, ANM–116, Transport Airplane 2017.
subsequent amendments can be viewed
Directorate, FAA, has the authority to Michael Kaszycki,
online at http://www.faa.gov/air_traffic/
approve AMOCs for this AD, if requested Acting Manager, Transport Airplane publications/. For further information,
using the procedures found in 14 CFR 39.19. Directorate, Aircraft Certification Service. you can contact the Airspace Policy
In accordance with 14 CFR 39.19, send your [FR Doc. 2017–10134 Filed 5–18–17; 8:45 am]
request to your principal inspector or local
Group, Federal Aviation
Flight Standards District Office, as
BILLING CODE 4910–13–P Administration, 800 Independence
appropriate. If sending information directly Avenue SW., Washington, DC, 20591;
to the International Branch, send it to ATTN: telephone: 202–267–8783. The Order is
Sanjay Ralhan, Aerospace Engineer, DEPARTMENT OF TRANSPORTATION also available for inspection at the
International Branch, ANM–116, Transport National Archives and Records
Airplane Directorate, FAA, 1601 Lind Federal Aviation Administration
Administration (NARA). For
Avenue SW., Renton, Washington 98057– information on the availability of FAA
3356; telephone 425–227–1405; fax 425–227– 14 CFR Part 71
Order 7400.11A at NARA, call 202–741–
1149. Information may be emailed to: 9- [Docket No. FAA–2017–0210; Airspace 6030, or go to http://www.archives.gov/
ANM-116-AMOC-REQUESTS@faa.gov. Docket No. 17–AGL–10]
(i) Before using any approved AMOC,
federal_register/code_of_federal-
notify your appropriate principal inspector, regulations/ibr_locations.html.
Proposed Amendment of Class D and FAA Order 7400.11, Airspace
or lacking a principal inspector, the manager
of the local flight standards district office/
E Airspace; Kenosha, WI Designations and Reporting Points, is
certificate holding district office. AGENCY: Federal Aviation published yearly and effective on
(ii) AMOCs approved previously for AD Administration (FAA), DOT. September 15.
2014–08–01 are approved as AMOCs for the FOR FURTHER INFORMATION CONTACT:
corresponding provisions of paragraphs (g) ACTION: Notice of proposed rulemaking
(NPRM). Jeffrey Claypool, Federal Aviation
and (h) of this AD. Administration, Operations Support
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement SUMMARY: This action proposes to Group, Central Service Center, 10101
in this AD to obtain corrective actions from modify Class D airspace, Class E Hillwood Parkway, Fort Worth, TX,
a manufacturer, the action must be airspace designated as a surface area, 76177; telephone 817–222–5711.
accomplished using a method approved by and Class E airspace extending upward SUPPLEMENTARY INFORMATION:
the Manager, International Branch, ANM– from 700 feet above the surface, and
116, Transport Airplane Directorate, FAA; or Authority for This Rulemaking
remove Class E airspace designated as
the European Aviation Safety Agency an extension of Class D airspace at The FAA’s authority to issue rules
(EASA); or Airbus’s EASA Design regarding aviation safety is found in
Kenosha Regional Airport, Kenosha, WI.
Organization Approval (DOA). If approved by Title 49 of the United States Code.
the DOA, the approval must include the The FAA is proposing this action due to
the decommissioning of the Kenosha Subtitle I, Section 106 describes the
DOA-authorized signature.
VHF omnidirectional range (VOR) authority of the FAA Administrator.
(3) Required for Compliance (RC): If any
service information contains procedures or facilities, which provided navigation Subtitle VII, Aviation Programs,
tests that are identified as RC, those guidance for portions of the affected describes in more detail the scope of the
procedures and tests must be done to comply routes. This action would enhance the agency’s authority. This rulemaking is
with this AD; any procedures or tests that are safety and management of instrument promulgated under the authority
not identified as RC are recommended. Those flight rules (IFR) operations at this described in Subtitle VII, Part A,
procedures and tests that are not identified
airport. Additionally, the airport name Subpart I, Section 40103. Under that
as RC may be deviated from using accepted section, the FAA is charged with
methods in accordance with the operator’s and geographic coordinates would be
adjusted in the Class E airspace prescribing regulations to assign the use
maintenance or inspection program without of airspace necessary to ensure the
obtaining approval of an AMOC, provided extending upward from 700 feet above
the surface to coincide with the FAA’s safety of aircraft and the efficient use of
the procedures and tests identified as RC can
be done and the airplane can be put back in aeronautical database. airspace. This regulation is within the
an airworthy condition. Any substitutions or scope of that authority as it would
DATES: Comments must be received on
changes to procedures or tests identified as amend Class D airspace, Class E
or before July 3, 2017. airspace designated as a surface area,
RC require approval of an AMOC.
ADDRESSES: Send comments on this and Class E airspace extending upward
(o) Related Information proposal to the U.S. Department of from 700 feet above the surface, as well
(1) Refer to Mandatory Continuing Transportation, Docket Operations, 1200
sradovich on DSK3GMQ082PROD with PROPOSALS
as remove Class E airspace designated as
Airworthiness Information (MCAI) EASA AD New Jersey Avenue SE., West Building an extension to Class D airspace at
2016–0113, dated June 15, 2016, for related Ground Floor, Room W12–140,
information. This MCAI may be found in the
Kenosha Regional Airport, Kenosha, WI,
Washington, DC 20590; telephone 202– to enhance the safety and management
AD docket on the Internet at http://
www.regulations.gov by searching for and
366–9826, or 1–800–647–5527. You of IFR operations at this airport..
locating Docket No. FAA–2017–0476. must identify FAA Docket No. FAA–
2017–0210; Airspace Docket No. 17– Comments Invited
(2) For service information identified in
this AD, contact Airbus, Airworthiness AGL–10 at the beginning of your Interested parties are invited to
Office—EIAS, 1 Rond Point Maurice comments. You may also submit participate in this proposed rulemaking
VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\19MYP1.SGM 19MYP1](https://thefederalregister.org/doc/82_FR_23014/page/5.svg)
Document Created: 2018-11-08 08:48:33
Document Modified: 2018-11-08 08:48:33
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by July 3, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227- 1405; fax 425-227-1149. | |
| FR Citation | 82 FR 22918 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR