82 FR 56859 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 230 (December 1, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 230 (December 1, 2017)
| Page Range | 56859-56865 | |
| FR Document | 2017-25557 |
[Federal Register Volume 82, Number 230 (Friday, December 1, 2017)] [Rules and Regulations] [Pages 56859-56865] From the Federal Register Online [www.thefederalregister.org] [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 [email protected]; 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: [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 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 [email protected]; 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
![56859
Rules and Regulations Federal Register
Vol. 82, No. 230
Friday, December 1, 2017
This section of the FEDERAL REGISTER The Director of the Federal Register Federal Register on May 19, 2017 (82
contains regulatory documents having general approved the incorporation by reference FR 22918).
applicability and legal effect, most of which of a certain other publication listed in The European Aviation Safety Agency
are keyed to and codified in the Code of this AD as of March 26, 2014 (79 FR (EASA), which is the Technical Agent
Federal Regulations, which is published under 9398, February 19, 2014). for the Member States of the European
50 titles pursuant to 44 U.S.C. 1510.
ADDRESSES: For service information Union, has issued EASA AD 2016–0113,
The Code of Federal Regulations is sold by identified in this final rule, contact dated June 15, 2016 (referred to after
the Superintendent of Documents. Airbus, Airworthiness Office—EIAS, 1 this as the Mandatory Continuing
Rond Point Maurice Bellonte, 31707 Airworthiness Information, or ‘‘the
Blagnac Cedex, France; telephone +33 5 MCAI’’), to correct an unsafe condition
DEPARTMENT OF TRANSPORTATION for all Airbus Model A318, A319, A320,
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; and A321 series airplanes. The MCAI
Federal Aviation Administration states:
Internet http://www.airbus.com. You
14 CFR Part 39 may view this referenced service The flap interconnecting strut is a safety
information at the FAA, Transport device of the High Lift System which acts as
[Docket No. FAA–2017–0476; Product Standards Branch, 1601 Lind Avenue an alternative load path from one flap surface
Identifier 2016–NM–110–AD; Amendment SW., Renton, WA. For information on to another in case of a flap drive system
39–19111; AD 2017–24–07] disconnection. In such a failure case, the
the availability of this material at the
installed proximity sensors provide
RIN 2120–AA64 FAA, call 425–227–1221. It is also information to the slat flap control computer
available on the Internet at http:// (SFCC) and the operation of the flap drive
Airworthiness Directives; Airbus www.regulations.gov by searching for system is inhibited.
Airplanes and locating Docket No. FAA–2017– An engineering investigation showed that,
0476. when a certain combination of target/sensor
AGENCY: Federal Aviation serial number (s/n) is installed on a flap
Administration (FAA), Department of Examining the AD Docket interconnecting strut, a ‘‘target FAR’’ signal
Transportation (DOT). cannot be detected when reaching the
You may examine the AD docket on
ACTION: Final rule. mechanical end stop of the interconnecting
the Internet at http://
strut.
www.regulations.gov by searching for This condition, if not corrected, could
SUMMARY: We are superseding
and locating Docket No. FAA–2017– cause a flap down drive disconnection to
Airworthiness Directive (AD) 2014–08–
0476; or in person at the Docket remain undetected, due to an already-failed
01, which applied to all Airbus Model
Management Facility between 9 a.m. interconnecting strut sensor, potentially
A318, A319, A320, and A321 series
and 5 p.m., Monday through Friday, resulting in asymmetric flap panel movement
airplanes. AD 2014–08–01 required an and consequent loss of control of the
except Federal holidays. The AD docket
inspection for part numbers of the aeroplane.
contains this AD, the regulatory
interconnecting struts and, for affected To address this potential unsafe condition,
evaluation, any comments received, and
interconnecting struts, identification of Airbus issued Service Bulletin (SB) A320–
other information. The address for the
the part and serial numbers of the 27–1206 and SB A320–57–1164, to provide
Docket Office (telephone 800–647–5527) identification and replacement instructions
associated target and proximity sensors
is Docket Management Facility, U.S. for struts that have a certain target/sensor s/
and replacement or re-identification of
Department of Transportation, Docket n combination installed. Aeroplanes on
the flap interconnecting strut if
Operations, M–30, West Building which modification (mod) 27956 had been
necessary. This AD continues to require
Ground Floor, Room W12–140, 1200 accomplished in production were identified
an inspection to verify the as not affected by the unsafe condition.
New Jersey Avenue SE., Washington,
interconnecting strut part number. This Consequently, EASA issued [EASA] AD
DC 20590.
AD also provides a new compliance 2012–0012 [which corresponds to FAA AD
time and an additional inspection for FOR FURTHER INFORMATION CONTACT: 2014–08–01] to require accomplishment of
previously inspected airplanes. This AD Sanjay Ralhan, Aerospace Engineer, these inspections and corrective actions.
was prompted by an investigation that International Section, Transport Since that [EASA] AD was issued, Airbus
showed that when a certain Standards Branch, FAA, 1601 Lind has informed EASA about a batch of
combination of target/proximity sensor Avenue SW., Renton, Washington aeroplanes that were delivered with pre-mod
serial numbers is installed on a flap 98057–3356; telephone 425–227–1405; 27956 Part Number (P/N) flap
fax 425–227–1149. interconnecting strut(s) installed, but
interconnecting strut, a ‘‘target FAR’’ declared to be in post-mod configuration in
signal cannot be detected when reaching SUPPLEMENTARY INFORMATION: the Aircraft Inspection Report. Airbus SB
the mechanical end stop of the A320–57–1202 has been issued to provide
interconnecting strut. We are issuing Discussion instructions to verify the interconnecting
this AD to address the unsafe condition We issued a notice of proposed strut P/N, and to update aircraft
jstallworth on DSKBBY8HB2PROD with RULES
on these products. rulemaking (NPRM) to amend 14 CFR documentation.
In addition, to ensure that all pre-mod
DATES: This AD is effective January 5, part 39 to supersede AD 2014–08–01,
parts are checked and corrected as required,
2018. Amendment 39–17825 (79 FR 23900, SB A320–27–1206 was revised to include a
The Director of the Federal Register April 29, 2014) (‘‘AD 2014–08–01’’). AD wider range of P/N of affected
approved the incorporation by reference 2014–08–01 applied to all Airbus Model interconnecting struts.
of a certain publication listed in this AD A318, A319, A320, and A321 series For the reasons described above, this
as of January 5, 2018. airplanes. The NPRM published in the [EASA] AD retains the requirements of EASA
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![56860 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations
AD 2012–0012, which is superseded, ‘‘wrapping’’ condition has led to installed interconnecting struts and the
expands the Applicability [adds affected part confusion in identifying the parts. part number and the serial number of
numbers], changes the compliance time and DAL stated that per the Airbus AIPC the associated target and proximity
requires an additional inspection for Front Matter, the 13th, 14th, and 15th sensor can be conclusively determined
aeroplanes that have already been inspected.
characters are controlled in specific from that review. We have revised
You may examine the MCAI in the ways. DAL also stated that the 13th and paragraph (i) of this AD accordingly.
AD docket on the Internet at http:// 14th characters are expected to be ‘‘00’’
www.regulations.gov by searching for and are used to fill out 12-digit base Conclusion
and locating Docket No. FAA–2017– numbers on the part installed during We reviewed the available data,
0476. production. DAL stated that the 15th including the comments received, and
Comments character is a paint code designator and determined that air safety and the
found the use of a paint code designator public interest require adopting this AD
We gave the public the opportunity to unusual on a part that is not viewable as proposed except for minor editorial
participate in developing this AD. The or expected to be painted to match an changes. We have determined that these
following presents the comments air carrier paint scheme. DAL minor changes:
received on the NPRM and the FAA’s commented that it believes the AD • Are consistent with the intent that
response to each comment. United should be updated to show 00A, 00B, or was proposed in the NPRM for
Airlines and the Air Line Pilots the list of true possibilities, and the correcting the unsafe condition; and
Association, International supported the XXX allowance creates a significant
NPRM. • Do not add any additional burden
number of possible part numbers that upon the public than was already
Request To Add Additional DAL must identify as prohibited. proposed in the NPRM.
Identification Steps We agree to clarify the requirement to
We also determined that these
identify affected parts. Regarding the
Delta Airlines (DAL) requested that changes will not increase the economic
characters in the part number,
additional identification steps be burden on any operator or increase the
identifying the last three characters are
required in the NPRM to ensure that the scope of this AD.
not required to identify a discrepant
affected parts are correctly identified. part; only the first twelve base numbers Related Service Information Under 1
DAL stated that figure 1 to paragraphs are required. Therefore, we do not agree CFR Part 51
(g) and (h) of the proposed AD contains to revise this AD to include a complete
part numbers for affected Airbus has issued Service Bulletin
list of all possible combinations of these
interconnecting struts. DAL commented A320–27–1206, Revision 02, dated
characters.
that a review of its records from November 2, 2015. The service
We acknowledge the commenter’s
inspections conducted during information describes procedures for an
concern about the ‘‘wrapping’’
compliance with AD 2014–08–01 inspection to determine the part number
condition for part identification.
determined that other part numbers of the installed interconnecting struts
However, in the photo provided by the
were possible. DAL stated that it has and the part number and serial number
commenter only the last three characters
had at least one instance of a part with of the associated target and proximity
are ‘‘wrapped.’’ As stated previously,
the part number D5757032200000A. sensors, and procedures for replacement
the last three characters are not required
DAL stated that figure 2 to paragraphs and re-identification of the
to identify a discrepant part.
(i)(2), (k), and (l) of the proposed AD interconnecting struts. This service
adds the provision that additional Formatting Change to a Figure information is reasonably available
alphanumeric characters may exist. DAL Figure 3 to paragraph (k)(1) of this AD because the interested parties have
commented that while the NPRM has been reformatted to clarify affected access to it through their normal course
removes some of the ambiguity that manufacturer serial numbers. of business or by the means identified
existed in AD 2014–08–01, a review of in the ADDRESSES section.
Airbus’s Aircraft Illustrated Parts Records Review
Costs of Compliance
Catalog (AIPC) does not show any parts We have determined that a review of
with a ‘‘letter’’ suffix. DAL provided a maintenance records is acceptable for We estimate that this AD affects 1,032
photo that showed that the part number complying with the actions specified in airplanes of U.S. registry.
appears to ‘‘wrap’’ (to the next line) on paragraphs (i)(1) and (i)(2) of this AD, We estimate the following costs to
the part. DAL stated that this provided the part number of the comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection and replacement (retained actions 8 work-hours × $85 per hour = $680 ............. $0 $680 $701,760
from AD 2014–08–01).
Inspection and replacement (new action) ....... 15 work-hours × $85 per hour = $1,275 ........ 0 1,275 1,315,800
We have received no definitive data Authority for This Rulemaking detail the scope of the Agency’s
jstallworth on DSKBBY8HB2PROD with RULES
that would enable us to provide cost Title 49 of the United States Code authority.
estimates for the on-condition actions specifies the FAA’s authority to issue We are issuing this rulemaking under
specified in this AD. rules on aviation safety. Subtitle I, the authority described in ‘‘Subtitle VII,
section 106, describes the authority of Part A, Subpart III, Section 44701:
the FAA Administrator. ‘‘Subtitle VII: General requirements.’’ Under that
Aviation Programs,’’ describes in more section, Congress charges the FAA with
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![Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations 56861
promoting safe flight of civil aircraft in Authority: 49 U.S.C. 106(g), 40113, 44701. Service Bulletin A320–27–1206, Revision 01,
air commerce by prescribing regulations dated October 10, 2011; or Airbus Service
§ 39.13 [Amended] Bulletin A320–27–1206, Revision 02, dated
for practices, methods, and procedures
the Administrator finds necessary for ■ 2. The FAA amends § 39.13 by November 2, 2015. A review of the airplane
safety in air commerce. This regulation removing Airworthiness Directive (AD) maintenance records is acceptable for
2014–08–01, Amendment 39–17825 (79 determining the part number of the installed
is within the scope of that authority
FR 23900, April 29, 2014), and adding interconnecting struts, in lieu of the
because it addresses an unsafe condition
inspection, if the part number of the installed
that is likely to exist or develop on the following new AD:
interconnecting struts, and the part number
products identified in this rulemaking 2017–24–07 Airbus: Amendment 39–19111; and the serial number of the associated target
action. Docket No. FAA–2017–0476; Product and proximity sensor, can be conclusively
This AD is issued in accordance with Identifier 2016–NM–110–AD. determined from that review.
authority delegated by the Executive (a) Effective Date Accomplishment of the requirements of
Director, Aircraft Certification Service, paragraph (i) of this AD terminates the
as authorized by FAA Order 8000.51C. This AD is effective January 5, 2018.
requirements of this paragraph.
In accordance with that order, issuance (b) Affected ADs (1) Airplanes on which Airbus
of ADs is normally a function of the This AD replaces AD 2014–08–01, Modification 27956 has been embodied in
Compliance and Airworthiness Amendment 39–17825 (79 FR 23900, April production, and on which no interconnecting
Division, but during this transition 29, 2014) (‘‘AD 2014–08–01’’). strut has been replaced with a strut having
period, the Executive Director has a part number specified in figure 1 to
(c) Applicability paragraphs (g) and (h) of this AD since the
delegated the authority to issue ADs
applicable to transport category This AD applies to Airbus Model A318– airplane’s first flight: No further work is
111, –112, –121, and –122 airplanes; Model required by paragraph (g) of this AD.
airplanes to the Director of the System
A319–111, –112, –113, –114, –115, –131, (2) If, during the inspection required by
Oversight Division. –132, and –133 airplanes; Model A320–211, paragraph (g) of this AD, any interconnecting
Regulatory Findings –212, –214, –231, –232, and –233 airplanes; strut is installed with a part number specified
and Model A321–111, –112, –131, –211, in figure 1 to paragraphs (g) and (h) of this
We determined that this AD will not –212, –213, –231, and –232 airplanes; AD: Within 8,000 flight hours after March 26,
have federalism implications under certificated in any category; all manufacturer 2014 (the effective date of AD 2014–03–08),
Executive Order 13132. This AD will serial numbers. determine the part number and the serial
not have a substantial direct effect on (d) Subject number of the associated target and
the States, on the relationship between proximity sensor.
the national government and the States, Air Transport Association (ATA) of
America Code 27, Flight controls. (i) For airplanes having conditions
or on the distribution of power and specified in paragraphs (g)(2)(i)(A),
responsibilities among the various (e) Reason (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this
levels of government. This AD was prompted by an investigation AD: Before further flight, replace the
For the reasons discussed above, I that showed that when a certain combination interconnecting strut with a serviceable unit,
certify that this AD: of target/proximity sensor serial numbers is in accordance with the Accomplishment
1. Is not a ‘‘significant regulatory installed on a flap interconnecting strut, a Instructions of Airbus Service Bulletin A320–
action’’ under Executive Order 12866; ‘‘target FAR’’ signal cannot be detected when 27–1206, Revision 01, dated October 10,
2. Is not a ‘‘significant rule’’ under the reaching the mechanical end stop of the 2011; or Airbus Service Bulletin A320–27–
DOT Regulatory Policies and Procedures interconnecting strut. We are issuing this AD 1206, Revision 02, dated November 2, 2015.
(44 FR 11034, February 26, 1979); to prevent an undetected flap down drive For the purposes of paragraph (g) of this AD,
3. Will not affect intrastate aviation in disconnection due to an already-failed a serviceable interconnecting strut is a unit
Alaska; and interconnecting strut sensor, which could that has been determined to be in compliance
result in asymmetric flap panel movement with the requirements of paragraph (g) of this
4. Will not have a significant
and consequent loss of control of the AD.
economic impact, positive or negative, airplane. (A) A target part number (P/N) ABS0121–
on a substantial number of small entities
(f) Compliance 13 or P/N 8–536–01; and
under the criteria of the Regulatory
(B) A target serial number lower than 1600,
Flexibility Act. Comply with this AD within the or a target serial number that is unreadable;
compliance times specified, unless already and
List of Subjects in 14 CFR Part 39 done.
(C) A proximity sensor having P/N
Air transportation, Aircraft, Aviation (g) Retained Inspection To Determine the ABS0121–31 or P/N 8–372–04; and
safety, Incorporation by reference, Part Number of the Interconnecting Struts, (D) A proximity sensor having a serial
Safety. With Revised Service Information number between C59198 and C59435, or a
Adoption of the Amendment This paragraph restates the requirements of serial number (S/N) C500000 or higher.
paragraph (g) of AD 2014–08–01, with (ii) For a target having S/N 1600 or higher
Accordingly, under the authority revised service information. Within 8,000 and target P/N ABS0121–13 or P/N 8–536–
delegated to me by the Administrator, flight hours after March 26, 2014 (the 01: Within 8,000 flight hours after March 26,
the FAA amends 14 CFR part 39 as effective date of AD 2014–03–08, 2014 (the effective date of AD 2014–03–08),
follows: Amendment 39–17745 (79 FR 9398, February re-identify the interconnecting strut, in
19, 2014) (‘‘AD 2014–03–08’’)), inspect to accordance with the Accomplishment
PART 39—AIRWORTHINESS determine the part number of the Instructions of Airbus Service Bulletin A320–
DIRECTIVES interconnecting struts installed on both the 27–1206, Revision 01, dated October 10,
left-hand (LH) and right-hand (RH) wings of 2011; or Airbus Service Bulletin A320–27–
jstallworth on DSKBBY8HB2PROD with RULES
■ 1. The authority citation for part 39 the airplane, in accordance with the 1206, Revision 02, dated November 2, 2015.
continues to read as follows: Accomplishment Instructions of Airbus BILLING CODE 4910–13–P
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![Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations 56865
Section, Transport Standards Branch, FAA, (3) The following service information was beam, lock fitting, and torsion box plate,
has the authority to approve AMOCs for this approved for IBR on January 5, 2018. and repair if necessary. This new AD
AD, if requested using the procedures found (i) Airbus Service Bulletin A320–27–1206, retains the inspections for cracking, and
in 14 CFR 39.19. In accordance with 14 CFR Revision 02, dated November 2, 2015.
39.19, send your request to your principal
repair if necessary; and requires
(ii) Reserved.
inspector or local Flight Standards District (4) The following service information was reinforcement of the aft cargo door sill
Office, as appropriate. If sending information approved for IBR on March 26, 2014 (79 FR beam area. This AD was prompted by
directly to the International Section, send it 9398, February 19, 2014). the development of a reinforcement
to the attention of the person identified in (i) Airbus Service Bulletin A320–27–1206, modification of the aft cargo door sill
paragraph (o)(2) of this AD. Information may Revision 01, dated October 10, 2011. beam area, which constitutes
be emailed to: 9-ANM-116-AMOC- (ii) Reserved. terminating action for the repetitive
REQUESTS@faa.gov. (5) For service information identified in inspections. We are issuing this AD to
(i) Before using any approved AMOC, this AD, contact Airbus, Airworthiness
notify your appropriate principal inspector, address the unsafe condition on these
Office—EIAS, 1 Rond Point Maurice
or lacking a principal inspector, the manager products.
Bellonte, 31707 Blagnac Cedex, France;
of the local flight standards district office/ telephone +33 5 61 93 36 96; fax +33 5 61 DATES: This AD is effective January 5,
certificate holding district office. 93 44 51; email account.airworth-eas@ 2018.
(ii) AMOCs approved previously for AD airbus.com; Internet http://www.airbus.com. The Director of the Federal Register
2014–08–01 are approved as AMOCs for the (6) You may view this service information
corresponding provisions of paragraphs (g)
approved the incorporation by reference
at the FAA, Transport Standards Branch, of a certain publication listed in this AD
and (h) of this AD. 1601 Lind Avenue SW., Renton, WA. For
(2) Contacting the Manufacturer: As of the as of July 2, 2014 (79 FR 34403, June 17,
information on the availability of this
effective date of this AD, for any requirement material at the FAA, call 425–227–1221.
2014).
in this AD to obtain corrective actions from (7) You may view this service information
The Director of the Federal Register
a manufacturer, the action must be that is incorporated by reference at the approved the incorporation by reference
accomplished using a method approved by National Archives and Records of certain other publications listed in
the Manager, International Section, Transport this AD as of January 3, 2017 (81 FR
Administration (NARA). For information on
Standards Branch, FAA; or the European 85837, November 29, 2016).
the availability of this material at NARA, call
Aviation Safety Agency (EASA); or Airbus’s
202–741–6030, or go to: http:// ADDRESSES: For service information
EASA Design Organization Approval (DOA).
www.archives.gov/federal-register/cfr/ibr- identified in this final rule, contact
If approved by the DOA, the approval must
locations.html.
include the DOA-authorized signature. Airbus SAS, Airworthiness Office—
(3) Required for Compliance (RC): If any Issued in Renton, Washington, on EAW, 1 Rond Point Maurice Bellonte,
service information contains procedures or November 16, 2017. 31707 Blagnac Cedex, France; telephone
tests that are identified as RC, those Chris Spangenberg, +33 5 61 93 36 96; fax +33 5 61 93 44
procedures and tests must be done to comply Acting Director, System Oversight Division, 51; email account.airworth-eas@
with this AD; any procedures or tests that are
Aircraft Certification Service. airbus.com; Internet http://
not identified as RC are recommended. Those
procedures and tests that are not identified [FR Doc. 2017–25557 Filed 11–30–17; 8:45 am] www.airbus.com. You may view this
as RC may be deviated from using accepted BILLING CODE 4910–13–P referenced service information at the
methods in accordance with the operator’s FAA, Transport Standards Branch, 1601
maintenance or inspection program without Lind Avenue SW., Renton, WA. For
obtaining approval of an AMOC, provided DEPARTMENT OF TRANSPORTATION information on the availability of this
the procedures and tests identified as RC can material at the FAA, call 425–227–1221.
be done and the airplane can be put back in Federal Aviation Administration It is also available on the Internet at
an airworthy condition. Any substitutions or
changes to procedures or tests identified as http://www.regulations.gov by searching
14 CFR Part 39 for and locating Docket No. FAA–2017–
RC require approval of an AMOC.
[Docket No. FAA–2017–0708; Product 0708.
(o) Related Information
Identifier 2017–NM–035–AD; Amendment Examining the AD Docket
(1) Refer to Mandatory Continuing 39–19113; AD 2017–24–09]
Airworthiness Information (MCAI) EASA AD You may examine the AD docket on
2016–0113, dated June 15, 2016, for related RIN 2120–AA64 the Internet at http://
information. This MCAI may be found in the www.regulations.gov by searching for
AD docket on the Internet at http:// Airworthiness Directives; Airbus and locating Docket No. FAA–2017–
www.regulations.gov by searching for and Airplanes
locating Docket No. FAA–2017–0476. 0708; or in person at the Docket
(2) For more information about this AD, AGENCY: Federal Aviation Management Facility between 9 a.m.
contact Sanjay Ralhan, Aerospace Engineer, Administration (FAA), Department of and 5 p.m., Monday through Friday,
International Section, Transport Standards Transportation (DOT). except Federal holidays. The AD docket
Branch, FAA, 1601 Lind Avenue SW.,
ACTION: Final rule.
contains this AD, the regulatory
Renton, Washington 98057–3356; telephone evaluation, any comments received, and
425–227–1405; fax 425–227–1149. SUMMARY: We are superseding other information. The address for the
(3) Service information identified in this Docket Office (telephone 800–647–5527)
AD that is not incorporated by reference is Airworthiness Directive (AD) 2016–20–
available at the addresses specified in 11, which applied to certain Airbus is Docket Management Facility, U.S.
paragraphs (p)(5) and (p)(6) of this AD. Model A300 B4–600, B4–600R, and F4– Department of Transportation, Docket
600R series airplanes, and Model A300 Operations, M–30, West Building
(p) Material Incorporated by Reference Ground Floor, Room W12–140, 1200
C4–605R Variant F airplanes
jstallworth on DSKBBY8HB2PROD with RULES
(1) The Director of the Federal Register (collectively called Model A300–600 New Jersey Avenue SE., Washington,
approved the incorporation by reference series airplanes); and Airbus Model DC 20590.
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
A310 series airplanes. AD 2016–20–11 FOR FURTHER INFORMATION CONTACT: Dan
part 51. required repetitive inspections of the Rodina, Aerospace Engineer,
(2) You must use this service information external area of the aft cargo door sill International Section, Transport
as applicable to do the actions required by beam for cracking, repetitive inspections Standards Branch, FAA, 1601 Lind
this AD, unless this AD specifies otherwise. for fatigue cracking of the cargo door sill Avenue SW., Renton, WA 98057–3356;
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Document Created: 2018-10-25 10:45:51
Document Modified: 2018-10-25 10:45:51
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective January 5, 2018. | |
| 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. | |
| FR Citation | 82 FR 56859 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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