Airworthiness Directives; Airbus Airplanes, 5362-5365 [2017-00408]

Download as PDF 5362 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations www.archives.gov/federal-register/cfr/ibrlocations.html. and locating Docket No. FAA–2015– 0831. Issued in Kansas City, Missouri, on January 6, 2017. Melvin Johnson, Manager, Small Airplane Directorate, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2017–00502 Filed 1–17–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0831; Directorate Identifier 2014–NM–061–AD; Amendment 39–18778; AD 2017–01–11] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. This AD requires identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 22, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 22, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet https://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. It is also available on the Internet at https:// www.regulations.gov by searching for mstockstill on DSK3G9T082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:39 Jan 17, 2017 Jkt 241001 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0831; 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 street 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 Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A318 and A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321 series airplanes. The SNPRM published in the Federal Register on June 28, 2016 (81 FR 41886) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on April 24, 2015 (80 FR 22939) (‘‘the NPRM’’). The NPRM proposed to require an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane; an inspection of the axle on certain MLG sliding tubes for damage; and replacement of the sliding tube if necessary. The NPRM was prompted by a report of a rupture of a MLG sliding tube axle. The SNPRM proposed to remove certain service information that does not adequately address the identified unsafe condition and revise the compliance method. We are issuing this AD to detect and correct cracks in the axle and (partial) detachment of the axle and wheel from the sliding tube, which could result in failure of an MLG. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Directive 2014–0058, dated March 11, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318 and A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321 series airplanes. The MCAI states: A main landing gear (MLG) sliding tube axle rupture occurred in service. Investigation of the affected part showed that this failure was due to an abnormal grinding operation during overhaul by a certain maintenance and repair organization located in Singapore. A population of MLG sliding tubes was subsequently identified whose axles may have been subject to this grinding operation, which may have resulted in areas of residual stress on the axles on the MLG sliding tubes. In addition, the MSN [manufacturer serial number] of the aeroplanes which are known to have had the affected parts installed have been identified. This condition, if not detected and corrected, could lead to cracks in the axle and (partial) detachment of axle and wheel from the sliding tube, possibly resulting in failure of a MLG with consequent damage to the aeroplane and injury to occupants. To address this potential unsafe condition, Messier-Bugatti-Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200–32–313 and SB 201–32–62 [both dated February 25, 2013], providing inspection instructions and criteria for removal from service of the affected MLG sliding tubes. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) of the axle on the affected MLG sliding tubes and, depending on findings, replacement of the MLG sliding tube. The SDI includes a detailed visual inspection of the chromium plate for damage, and a Barkhausen noise inspection of the sliding tube axles for damage. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0831. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data 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 SNPRM for correcting the unsafe condition; and E:\FR\FM\18JAR1.SGM 18JAR1 5363 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations • Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. This service information describes procedures for inspecting MLG axles and brake flanges by doing a detailed visual inspection of the chromium plates for damage, a Barkhausen noise inspection of the sliding tube axles for damage, and replacement of affected parts if necessary. 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 3 airplanes of U.S. registry. We also estimate that it would take about 18 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $4,590, or $1,530 per product. In addition, we estimate that any necessary on-condition actions will take about 3 work-hours, for a cost of $255 per product. We have received no definitive data that would enable us to provide part cost estimates for the oncondition actions specified in this AD. We have no way of determining the number of aircraft that might need these actions. 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 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–01–11 Airbus: Amendment 39–18778; Docket No. FAA–2015–0831; Directorate Identifier 2014–NM–061–AD. (a) Effective Date This AD is effective February 22, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. We are issuing this AD to detect and correct cracks in the axle and (partial) detachment of the axle and wheel from the sliding tube, which could result in failure of an MLG. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) MLG Sliding Tube Part Number and Serial Number Identification Within 3 months after the effective date of this AD: Do an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the MLG sliding tubes can be conclusively determined from that review. (h) Identification of Airplanes Not Affected by the Requirements of Paragraph (i) of this AD An airplane with a manufacturer serial number (MSN) not listed in figure 1 to paragraph (h) of this AD is not affected by the requirements of paragraph (i) of this AD, provided it can be determined that no MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD has been installed on that airplane since first flight of the airplane. mstockstill on DSK3G9T082PROD with RULES FIGURE 1 TO PARAGRAPH (H) OF THIS AD Affected Airplanes Listed by MSN 0179 0607 0754 0909 1030 VerDate Sep<11>2014 0214 0668 0771 0914 1041 16:39 Jan 17, 2017 Jkt 241001 0296 0704 0799 0925 1070 PO 00000 Frm 00029 0412 0720 0828 0939 1083 Fmt 4700 Sfmt 4700 E:\FR\FM\18JAR1.SGM 0558 0726 0841 0986 1093 18JAR1 0604 0731 0855 1028 1098 5364 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations FIGURE 1 TO PARAGRAPH (H) OF THIS AD—Continued 1108 1148 1294 TABLE 1 TO PARAGRAPHS (h), (i), (k)(1), (k)(2), (l)(1), AND (l)(2) OF THIS AD—AFFECTED MLG SLIDING TUBES mstockstill on DSK3G9T082PROD with RULES Part No. 201160302 201160302 201160302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201160302 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201522353 201522350 201522350 201522350 201522350 201522350 201522353 201522353 201522353 201522353 201522353 201383350 201383350 201383350 201383350 201383350 201383350 ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ Serial No. 78B 1016B11 1144B B4493 B4513 SS4359 B4530 B4517 B4568 B4498 4490B B202–4598 B165–4623 B244–4766 B267–4794 B272–4813 1108B B041–4871 B045–4869 B001–4781 B051–4892 B110–1952 B054–4891 B063–4921 B071–4911 B071–4917 B080–1933 B117–5010 B120–4989 B132–2023 B114–1956 B208–2009 B133–1947 B154–5037 B89 4952 B129–1964 B227–2010 B170–5031 B182–5047 B239–2053 B1401–2856 B1813–3142 B116–5004 B011–149 B014–25 B019–56 B019–57 B021–69 B022–60 B03–111 B03–110 B112–317 B174–351 B179–392 4377B 4393B B1831 B1832 SS4355B SS4400B (i) Inspections For each MLG sliding tube identified as required by paragraph (g) of this AD, having VerDate Sep<11>2014 16:39 Jan 17, 2017 Jkt 241001 1356 a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: Within 3 months after the effective date of this AD, inspect affected MLG axles and brake flanges by doing a detailed visual inspection of the chromium plates for damage, and a Barkhausen noise inspection of the sliding tube axles for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320– 32–1416, including Appendix 01, dated March 10, 2014. (j) Corrective Action If, during any inspection required by paragraph (i) of this AD, any damage is detected: Before further flight, replace the MLG sliding tube with a serviceable tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. (k) Definition of Serviceable Sliding Tube For the purpose of this AD, a serviceable sliding tube is defined as a sliding tube that meets the criterion in either paragraph (k)(1) or (k)(2) of this AD. (1) A sliding tube having a part number and serial number not listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD. (2) A sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD that has passed the inspections required by paragraph (i) of this AD. (l) Parts Installation Prohibitions (1) For airplanes that have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an airplane is returned to service following accomplishment of the actions required by paragraphs (g), (h), and (i) of this AD, no person may install on any airplane an MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD unless that sliding tube has passed the inspection required by paragraph (i) of this AD. (2) For airplanes that, as of the effective date of this AD, do not have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: No person may install on any airplane an MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 2713 2831 (l)(2) of this AD unless that sliding tube has passed the inspection required by paragraph (i) of this AD. (m) 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, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9–ANM–116– AMOC–REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) 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. (3) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (n) Special Flight Permits Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided the MLG remains extended throughout the flight. (o) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA E:\FR\FM\18JAR1.SGM 18JAR1 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations Airworthiness Directive 2014–0058, dated March 11, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2015–0831. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 4, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–00408 Filed 1–17–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9058; Directorate Identifier 2016–NM–024–AD; Amendment 39–18771; AD 2017–01–04] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. mstockstill on DSK3G9T082PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by an analysis which determined that, SUMMARY: VerDate Sep<11>2014 16:39 Jan 17, 2017 Jkt 241001 for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. This AD requires one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 22, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 22, 2017. ADDRESSES: For service information identified in this final rule, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone: +31 (0)88–6280–350; fax: +31 (0)88– 6280–111; email: technicalservices@ fokker.com; Internet https:// www.myfokkerfleet.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. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9058. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9058; 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 street 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425 227 1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 5365 apply to certain Fokker Services B.V. Model F28 Mark 0100 airplanes. The NPRM published in the Federal Register on September 8, 2016 (81 FR 62029) (‘‘the NPRM’’). The NPRM was prompted by an analysis which determined that, for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. The NPRM proposed to require one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to detect and correct cracks in the fuselage skin; such cracking could result in reduced structural integrity of the fuselage. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive Airworthiness Directive 2016– 0029R1, dated November 17, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. The MCAI states: A complementary fatigue and damage tolerance analysis was accomplished by the design approval holder on the traffic collision avoidance system (TCAS) antenna installation on the top of the fuselage between station (STA) 6805 and STA7305. Based on the results, it was determined that for the affected area, the current 58 000 flight cycles (FC) threshold of Airworthiness Limitations Section (ALS) inspection task 533001–00–20 and 533028–00–20 (special detailed inspection of longitudinal lap joints) is insufficient to timely detect possible crack development. This condition, if not detected and corrected, could affect the structural integrity of the fuselage in this area. To address this potential unsafe condition, Fokker Services published Service Bulletin (SB) SBF100–53–130 to provide inspection instructions. Consequently, EASA issued AD 2016–0029 to require a one-time inspection of the fuselage skin around the largest TCAS antenna external doubler and of the longitudinal lap joint at stringer (STR) 37 between fuselage STA6805 and STA7305. Since that [EASA] AD was issued, it was discovered that another ALS inspection task, 533028–00–20, is also related to this subject. This [EASA] AD is revised to clarify that the inspection threshold of both ALS inspection tasks has been re-assessed. It is expected that a repetitive inspection task will be included in the ALS, which will cover only the area close to the TCAS antenna installation. For the remainder of the affected lap joint, no change is anticipated and this will therefore continue to be inspected in accordance with the existing ALS tasks. This [EASA] AD is still considered to be an interim action and further [EASA] AD E:\FR\FM\18JAR1.SGM 18JAR1

Agencies

[Federal Register Volume 82, Number 11 (Wednesday, January 18, 2017)]
[Rules and Regulations]
[Pages 5362-5365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-00408]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0831; Directorate Identifier 2014-NM-061-AD; 
Amendment 39-18778; AD 2017-01-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A318 and A319 series airplanes, Model A320-211, -212, -
214, -231, -232, and -233 airplanes, and Model A321 series airplanes. 
This AD was prompted by a report of a rupture of a main landing gear 
(MLG) sliding tube axle. This AD requires identification of the part 
number and serial number of the MLG sliding tubes; inspection of 
affected chromium plates and sliding tube axles for damage; and 
replacement of the sliding tube if necessary. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective February 22, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 22, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
https://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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0831.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0831; 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 street 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 Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to all Airbus 
Model A318 and A319 series airplanes, Model A320-211, -212, -214, -231, 
-232, and -233 airplanes, and Model A321 series airplanes. The SNPRM 
published in the Federal Register on June 28, 2016 (81 FR 41886) (``the 
SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking 
(NPRM) that published in the Federal Register on April 24, 2015 (80 FR 
22939) (``the NPRM''). The NPRM proposed to require an inspection to 
identify the part number and serial number of the MLG sliding tubes 
installed on the airplane; an inspection of the axle on certain MLG 
sliding tubes for damage; and replacement of the sliding tube if 
necessary. The NPRM was prompted by a report of a rupture of a MLG 
sliding tube axle. The SNPRM proposed to remove certain service 
information that does not adequately address the identified unsafe 
condition and revise the compliance method. We are issuing this AD to 
detect and correct cracks in the axle and (partial) detachment of the 
axle and wheel from the sliding tube, which could result in failure of 
an MLG.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0058, dated March 11, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A318 
and A319 series airplanes, Model A320-211, -212, -214, -231, -232, and 
-233 airplanes, and Model A321 series airplanes. The MCAI states:

    A main landing gear (MLG) sliding tube axle rupture occurred in 
service. Investigation of the affected part showed that this failure 
was due to an abnormal grinding operation during overhaul by a 
certain maintenance and repair organization located in Singapore. A 
population of MLG sliding tubes was subsequently identified whose 
axles may have been subject to this grinding operation, which may 
have resulted in areas of residual stress on the axles on the MLG 
sliding tubes. In addition, the MSN [manufacturer serial number] of 
the aeroplanes which are known to have had the affected parts 
installed have been identified.
    This condition, if not detected and corrected, could lead to 
cracks in the axle and (partial) detachment of axle and wheel from 
the sliding tube, possibly resulting in failure of a MLG with 
consequent damage to the aeroplane and injury to occupants.
    To address this potential unsafe condition, Messier-Bugatti-
Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200-
32-313 and SB 201-32-62 [both dated February 25, 2013], providing 
inspection instructions and criteria for removal from service of the 
affected MLG sliding tubes.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) of the axle on the affected 
MLG sliding tubes and, depending on findings, replacement of the MLG 
sliding tube.

    The SDI includes a detailed visual inspection of the chromium plate 
for damage, and a Barkhausen noise inspection of the sliding tube axles 
for damage.
    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0831.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

    We reviewed the relevant data 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 
SNPRM for correcting the unsafe condition; and

[[Page 5363]]

     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-32-1416, including Appendix 
01, dated March 10, 2014. This service information describes procedures 
for inspecting MLG axles and brake flanges by doing a detailed visual 
inspection of the chromium plates for damage, a Barkhausen noise 
inspection of the sliding tube axles for damage, and replacement of 
affected parts if necessary. 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 3 airplanes of U.S. registry.
    We also estimate that it would take about 18 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $4,590, or $1,530 per product.
    In addition, we estimate that any necessary on-condition actions 
will take about 3 work-hours, for a cost of $255 per product. We have 
received no definitive data that would enable us to provide part cost 
estimates for the on-condition actions specified in this AD. We have no 
way of determining the number of aircraft that might need these 
actions.

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 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 adding the following new airworthiness 
directive (AD):

2017-01-11 Airbus: Amendment 39-18778; Docket No. FAA-2015-0831; 
Directorate Identifier 2014-NM-061-AD.

(a) Effective Date

    This AD is effective February 22, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
gear.

(e) Reason

    This AD was prompted by a report of a rupture of a main landing 
gear (MLG) sliding tube axle. We are issuing this AD to detect and 
correct cracks in the axle and (partial) detachment of the axle and 
wheel from the sliding tube, which could result in failure of an 
MLG.

(f) Compliance

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

(g) MLG Sliding Tube Part Number and Serial Number Identification

    Within 3 months after the effective date of this AD: Do an 
inspection to identify the part number and serial number of the MLG 
sliding tubes installed on the airplane. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part number and serial number of the MLG sliding tubes can be 
conclusively determined from that review.

(h) Identification of Airplanes Not Affected by the Requirements of 
Paragraph (i) of this AD

    An airplane with a manufacturer serial number (MSN) not listed 
in figure 1 to paragraph (h) of this AD is not affected by the 
requirements of paragraph (i) of this AD, provided it can be 
determined that no MLG sliding tube having a part number and serial 
number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), 
(l)(1), and (l)(2) of this AD has been installed on that airplane 
since first flight of the airplane.

                                      Figure 1 to Paragraph (h) of This AD
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
                                        Affected Airplanes Listed by MSN
----------------------------------------------------------------------------------------------------------------
           0179               0214               0296               0412               0558               0604
           0607               0668               0704               0720               0726               0731
           0754               0771               0799               0828               0841               0855
           0909               0914               0925               0939               0986               1028
           1030               1041               1070               1083               1093               1098

[[Page 5364]]

 
           1108               1148               1294               1356               2713               2831
----------------------------------------------------------------------------------------------------------------


  Table 1 to Paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of
                   this AD--Affected MLG Sliding Tubes
------------------------------------------------------------------------
                        Part No.                            Serial No.
------------------------------------------------------------------------
201160302...............................................             78B
201160302...............................................         1016B11
201160302...............................................           1144B
201371302...............................................           B4493
201371302...............................................           B4513
201371302...............................................          SS4359
201371302...............................................           B4530
201371302...............................................           B4517
201371302...............................................           B4568
201371302...............................................           B4498
201371302...............................................           4490B
201371302...............................................       B202-4598
201371302...............................................       B165-4623
201371302...............................................       B244-4766
201371302...............................................       B267-4794
201371302...............................................       B272-4813
201160302...............................................           1108B
201371304...............................................       B041-4871
201371304...............................................       B045-4869
201371304...............................................       B001-4781
201371304...............................................       B051-4892
201371304...............................................       B110-1952
201371304...............................................       B054-4891
201371304...............................................       B063-4921
201371304...............................................       B071-4911
201371304...............................................       B071-4917
201371304...............................................       B080-1933
201371304...............................................       B117-5010
201371304...............................................       B120-4989
201371304...............................................       B132-2023
201371304...............................................       B114-1956
201371304...............................................       B208-2009
201371304...............................................       B133-1947
201371304...............................................       B154-5037
201371304...............................................        B89 4952
201371304...............................................       B129-1964
201371304...............................................       B227-2010
201371304...............................................       B170-5031
201371304...............................................       B182-5047
201371304...............................................       B239-2053
201371304...............................................      B1401-2856
201371304...............................................      B1813-3142
201371304...............................................       B116-5004
201522353...............................................        B011-149
201522350...............................................         B014-25
201522350...............................................         B019-56
201522350...............................................         B019-57
201522350...............................................         B021-69
201522350...............................................         B022-60
201522353...............................................         B03-111
201522353...............................................         B03-110
201522353...............................................        B112-317
201522353...............................................        B174-351
201522353...............................................        B179-392
201383350...............................................           4377B
201383350...............................................           4393B
201383350...............................................           B1831
201383350...............................................           B1832
201383350...............................................         SS4355B
201383350...............................................         SS4400B
------------------------------------------------------------------------

(i) Inspections

    For each MLG sliding tube identified as required by paragraph 
(g) of this AD, having a part number and serial number listed in 
table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) 
of this AD: Within 3 months after the effective date of this AD, 
inspect affected MLG axles and brake flanges by doing a detailed 
visual inspection of the chromium plates for damage, and a 
Barkhausen noise inspection of the sliding tube axles for damage, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014. 
For Model A318 series airplanes, use the procedures specified for 
Model A319 series airplanes in Airbus Service Bulletin A320-32-1416, 
including Appendix 01, dated March 10, 2014.

(j) Corrective Action

    If, during any inspection required by paragraph (i) of this AD, 
any damage is detected: Before further flight, replace the MLG 
sliding tube with a serviceable tube, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-32-1416, 
including Appendix 01, dated March 10, 2014. For Model A318 series 
airplanes, use the procedures specified for Model A319 series 
airplanes in Airbus Service Bulletin A320-32-1416, including 
Appendix 01, dated March 10, 2014.

(k) Definition of Serviceable Sliding Tube

    For the purpose of this AD, a serviceable sliding tube is 
defined as a sliding tube that meets the criterion in either 
paragraph (k)(1) or (k)(2) of this AD.
    (1) A sliding tube having a part number and serial number not 
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), 
and (l)(2) of this AD.
    (2) A sliding tube having a part number and serial number listed 
in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 
(l)(2) of this AD that has passed the inspections required by 
paragraph (i) of this AD.

(l) Parts Installation Prohibitions

    (1) For airplanes that have an MLG sliding tube installed that 
has a part number and serial number listed in table 1 to paragraphs 
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an 
airplane is returned to service following accomplishment of the 
actions required by paragraphs (g), (h), and (i) of this AD, no 
person may install on any airplane an MLG sliding tube having a part 
number and serial number listed in table 1 to paragraphs (h), (i), 
(k)(1), (k)(2), (l)(1), and (l)(2) of this AD unless that sliding 
tube has passed the inspection required by paragraph (i) of this AD.
    (2) For airplanes that, as of the effective date of this AD, do 
not have an MLG sliding tube installed that has a part number and 
serial number listed in table 1 to paragraphs (h), (i), (k)(1), 
(k)(2), (l)(1), and (l)(2) of this AD: No person may install on any 
airplane an MLG sliding tube having a part number and serial number 
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), 
and (l)(2) of this AD unless that sliding tube has passed the 
inspection required by paragraph (i) of this AD.

(m) 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, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) 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.
    (3) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(n) Special Flight Permits

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified (if the operator elects to do so), provided the MLG 
remains extended throughout the flight.

(o) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA

[[Page 5365]]

Airworthiness Directive 2014-0058, dated March 11, 2014, for related 
information. This MCAI may be found in the AD docket on the Internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2015-0831.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-32-1416, including Appendix 01, 
dated March 10, 2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 4, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-00408 Filed 1-17-17; 8:45 am]
 BILLING CODE 4910-13-P

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