Airworthiness Directives; Airbus SAS Airplanes, 47047-47053 [2018-19854]

Download as PDF Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations (3) For Models 35, 35A, 36, and 36A airplanes: Within 24 months after October 23, 2018 (the effective date of this AD) or within 400 landings after October 23, 2018 (the effective date of this AD), whichever occurs first, replace the nose roller fitting, nose roller support bracket, and adjacent rib support structure with replacement parts by following the Accomplishment Instructions in Bombardier Learjet 35/36 SB 35/36–27–50 Recommended, dated September 11, 2017. (4) For Models 55, 55B, and 55C airplanes: Within 24 months after October 23, 2018 (the effective date of this AD) or within 400 landings after October 23, 2018 (the effective date of this AD), whichever occurs first, replace the nose roller fitting, nose roller support bracket, and adjacent rib support structure with replacement parts by following the Accomplishment Instructions in Bombardier Learjet 55 SB 55–27–41 Recommended, dated September 11, 2017. (5) For Model 60 airplanes: Within 12 months after October 23, 2018 (the effective date of this AD) or within 200 landings after October 23, 2018 (the effective date of this AD), whichever occurs first, replace the nose roller fitting, nose roller support bracket, and adjacent rib support structure with replacement parts by following the Accomplishment Instructions in Bombardier Learjet 60 SB 60–27–39 Recommended, Revision 1, dated January 15, 2018. (6) For all airplanes: Some compliance times in this AD are presented in landings. If you do not keep a record of the total number of landings, then use a 1-to-1 conversion for hours time-in-service (TIS) to landings. Example: 20 hours TIS = 20 landings. (7) For Models 31, 31A, 35, 35A, 36, 36A, 55, 55B, 55C, and 60 airplanes: Although Paragraph 3.B.(2) of the applicable SB for these models that have modified flap roller assemblies requires the operator to contact Learjet Inc. for repair instructions, this AD requires you do the repair using a method approved by the Manager, Wichita ACO Branch, FAA. For a repair method to be approved by the Manager, Wichita ACO Branch, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. daltland on DSKBBV9HB2PROD with RULES (h) Credit for Previous Actions For Model 60 airplanes: This AD allows credit for actions required in paragraph (g)(5) of this AD if done before the effective date of this AD following Bombardier Learjet 60 SB 60–27–39 Recommended, Basic Issue, dated September 11, 2017. (i) No Reporting Requirement Although Bombardier Learjet 28/29 SB 28/ 29–27–31 Recommended, dated September 11, 2017; Bombardier Learjet 31 SB 31–27– 35 Recommended, dated September 11, 2017; Bombardier Learjet 35/36 SB 35/36 –27–50 Recommended, dated September 11, 2017; Bombardier Learjet 55 SB 55–27–41 Recommended, dated September 11, 2017; and Bombardier Learjet 60 SB 60–27–39 Recommended, Revision 1, dated January 15, 2018, all specify to submit a compliance response form to the manufacturer per paragraph 3.E., this AD does not require that action. VerDate Sep<11>2014 16:42 Sep 17, 2018 Jkt 244001 (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita ACO 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 manager of the certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD. (2) 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. 47047 Issued in Kansas City, Missouri, on August 31, 2018. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–19853 Filed 9–17–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0390; Product Identifier 2017–NM–130–AD; Amendment 39–19397; AD 2018–18–18] (k) Related Information RIN 2120–AA64 For more information about this AD, contact Tara Shawn, Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4141; fax: (316) 946–4107; email: tara.shawn@faa.gov or Wichita-COS@faa.gov. Airworthiness Directives; Airbus SAS Airplanes (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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 the AD specifies otherwise. (i) Bombardier Learjet 28/29 Service Bulletin (SB) 28/29–27–31 Recommended, dated September 11, 2017; (ii) Bombardier Learjet 31 SB 31–27–35 Recommended, dated September 11, 2017; (iii) Bombardier Learjet 35/36 SB 35/36 –27–50 Recommended, dated September 11, 2017; (iv) Bombardier Learjet 55 SB 55–27–41 Recommended, dated September 11, 2017; and (v) Bombardier Learjet 60 SB 60–27–39 Recommended, Revision 1, dated January 15, 2018. (3) For service information identified in this AD, contact Learjet, Inc., One Learjet Way, Wichita, Kansas 67209; telephone: 316– 946–2000; email: ac.ict@ aero.bombardier.com; internet: https:// www.bombardier.com. (4) You may view this service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. In addition, you can access this service information on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017–1078. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a revision of an airworthiness limitation items (ALI) document. This AD requires revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 23, 2018. ADDRESSES: SUMMARY: 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–2018– 0390; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225. SUPPLEMENTARY INFORMATION: E:\FR\FM\18SER1.SGM 18SER1 47048 Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations Discussion daltland on DSKBBV9HB2PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus SAS Model A300 series airplanes. The NPRM published in the Federal Register on May 11, 2018 (83 FR 21955). The NPRM was prompted by a revision of an ALI document. The NPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the reduced structural integrity of the airplane and possible loss of controllability of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0145, dated August 31, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A300 series airplanes. The MCAI states: Some airworthiness limitations previously defined in A300 ALS [Airworthiness Limitations Section] Part 1 have been removed from that document and should normally be included in an ALS Part 4. Airbus does not plan to issue an ALS Part 4 for A300 aeroplanes. Nevertheless, failure to comply with these airworthiness limitations could result in an unsafe condition. For the reason described above, it has been decided to require the application of these airworthiness limitations through a separate AD. Previously, EASA issued AD 2013–0210 [which corresponds to FAA AD 2014–16–13, Amendment 39–17937 (79 FR 51083, August 27, 2014) (‘‘AD 2014–16–13’’)] to require implementation of airworthiness limitations applicable to main landing gear (MLG) barrel assembly, retraction actuator assembly, linkage assembly and flanged duct, which were previously defined in Revision 00 of A300 ALS Part 1 but removed from Revision 01 of A300 ALS Part 1, adding those limits as an Appendix to the AD. Since EASA AD 2013–0210 was issued, improvement of safe life component selection resulted, among others, in removal of 15 nose landing gear (NLG) parts from Revision 02 of A300 ALS Part 1. Consequently, this [EASA] AD retains the requirements of EASA AD 2013–0210, which is superseded, and requires, in addition to the implementation of airworthiness limitations already contained in EASA AD 2013–0210, the implementation of airworthiness limitations applicable to NLG barrel assembly and shock absorber assembly, previously contained in Revision 01 of A300 ALS Part 1, as specified in Appendix 1 of this AD. VerDate Sep<11>2014 16:42 Sep 17, 2018 Jkt 244001 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–2018– 0390. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA’s response to the comment. Request To Supersede AD 2014–16–13 Airbus questioned the need to keep AD 2014–16–13 and whether the proposed AD should instead supersede AD 2014–16–13. Airbus noted that the proposed AD lists all of the ALIs in EASA AD 2017–0145, dated August 31, 2017, not just the ALIs that have been updated since we issued AD 2014–16– 13. We infer that Airbus wanted the proposed AD changed to a supersedure AD. We disagree with the request to change this AD to a supersedure AD. To address the unsafe condition, we chose to match EASA AD 2017–0145, dated August 31, 2017, and include the same ALIs. Because accomplishment of the requirements of this AD terminates all requirements of AD 2014–16–13, a supersedure is not necessary. We have not changed this AD in this regard. Request To Release Related ADs at the Same Time Airbus requested that we release this final rule at the same time as the following related ADs to provide clarity to operators. All four pending ADs are related to the same removal of 15 nose landing gear parts from ALS Part 1, on different airplane models. • Docket No. FAA–2018–0364, Product Identifier 2017–NM–154–AD (EASA AD 2017–0204, dated October 12, 2017). • Docket No. FAA–2018–0365, Product Identifier 2017–NM–155–AD (EASA AD 2017–0203, dated October 12, 2017). • Docket No. FAA–2018–0396, Product Identifier 2017–NM–156–AD (EASA AD 2017–0202, dated October 12, 2017). We agree with the request insofar as we can control the publication schedule. While we cannot ensure that all four will be published on the same date, we will coordinate with the Office of the Federal Register (OFR) and attempt to issue all four final rules at the same time. Conclusion We reviewed the relevant data, considered the comments received, and PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing 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 final rule. Costs of Compliance We estimate that this AD affects 5 airplanes of U.S. registry. We estimate the following costs to comply with this AD: We have determined that revising the maintenance or inspection program takes an average of 90 work-hours per operator, although we recognize that this number may vary from operator to operator. In the past, we have estimated that this action takes 1 work-hour per airplane. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), we have determined that a per-operator estimate is more accurate than a perairplane estimate. Therefore, we estimate the total cost per operator to be $7,650 (90 work-hours × $85 per workhour). 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. 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 E:\FR\FM\18SER1.SGM 18SER1 Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings daltland on DSKBBV9HB2PROD with RULES 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. VerDate Sep<11>2014 16:42 Sep 17, 2018 Jkt 244001 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): ■ 2018–18–18 Airbus SAS: Amendment 39– 19397; Docket No. FAA–2018–0390; Product Identifier 2017–NM–130–AD. (a) Effective Date This AD is effective October 23, 2018. (b) Affected ADs This AD affects AD 2014–16–13, Amendment 39–17937 (79 FR 51083, August 27, 2014) (‘‘AD 2014–16–13’’). (c) Applicability This AD applies to Airbus SAS Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 47049 2C, B4–103, and B4–203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 05, Time Limits/Maintenance Checks. (e) Reason This AD was prompted by a revision of an airworthiness limitation items (ALI) document. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Revision of Maintenance or Inspection Program Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the safe life limits included in figure 1 to paragraph (g) of this AD. The initial compliance time for the replacements is prior to the applicable life limits specified in figure 1 to paragraph (g) of this AD, or within 90 days after the effective date of this AD, whichever occurs later. The term ‘‘FH’’ in figure 1 to paragraph (g) of this AD means total flight hours. The term ‘‘LDG’’ in figure 1 to paragraph (g) of this AD means total airplane landings. BILLING CODE 4910–13–P E:\FR\FM\18SER1.SGM 18SER1 47050 Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations Figure 1 to paragraph (g) of this AD- New Life Limits for the Main Landing Gear (MLG) Barrel Assembly, Retraction Actuator Assembly, Linkage Assembly; Pneumatic Flange Duct; Nose Landing Gear (NLG) Barrel Assembly and Shock Absorber Assembly SAFE LIFE LIMITS (*) Part Number FH ATA 32-1~0 MAIN LANDING GEAR BARREL ASSEMBLY C66277-10 NJA Stirrup C66277-12 Cal 66600 N/A X X X X 76600 N/A X X X X 76600 N/A X X X X 76600 N/A X X X X C66457 N/A 76600 N/A X X X X 048939 NJA 76600 N/A X X X X 048939-1 N/A 76600 N/A X X X X 058314-1 NJA 76600 N/A X X X X C66279 NJA 76600 N/A X X X X C66279-2 NJA 76600 N/A X X X X C66279-6 NJA 76600 N/A X X X X 058313-1 NJA 76600 N/A X X X X C61637-10 N/A 76600 N/A X X C61637-11 X NJA 76600 N/A X C61637-12 N/A 76600 N/A X X C61638-10 N/A 53300 N/A X X C61638-11 N/A 53300 N/A X X C61638-20 NJA 76600 N/A X X C68523-3 NJA 76600 N/A X X X C69028-4 N/A 34000 N/A C69029-1 (1) N/A 32000 N/A X X X X C69029-2 N/A 32000 N/A X X X X C69029-3 N/A 32000 N/A X N/A 22000 N/A X C67078 NJA 33000 N/A X X X X X X C69029-4 (2) X X C67078-1 N/A 33000 N/A X X X X C61342-4 NJA 36700 N/A C66510-4 NJA 32000 N/A X X X X PO 00000 Frm 00024 Piston End fitting daltland on DSKBBV9HB2PROD with RULES B4-1xx NJA RETRACTION ACTUATOR ASSEMBLY (1) When SB Al00-32-0123 embodied before SB Al00-32-0113. I (2) When SB AJ00-32..0123 embodied after SB Al00-32..0113. C69028-1 N/A N/A 34000 X VerDate Sep<11>2014 C4-203 F4-203 LOG N/A Tie rod Sliding rod Affected Model(s) B4-2C 84_2xx 82-320 058303-1 Universal joint Plate (Rear head end) 82K-3C B2-20x C66277-14 Stirrup pin Plate (Upper end) NJA B2-1A B2-1C 16:42 Sep 17, 2018 Jkt 244001 Fmt 4700 X X Sfmt 4725 X X X X E:\FR\FM\18SER1.SGM 18SER1 ER18SE18.001</GPH> Part Name 47051 Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations LINKAGE ASSEMBLY C61505 NIA 76600 N/A Upper X X multiple link C61505-1 N/A X NIA 76600 X pin (Multiple link/Upper C61505-20 NIA 76600 NIA X X linkS ATA36-11-05 PNEUMATIC (1) "xx" at the end of the PIN stands for anv number between 00 and 99. Duct flanged ( 1) A2127~~63000 N/A 24000 N/A X X X End fitting pin End fitting daltland on DSKBBV9HB2PROD with RULES Rack VerDate Sep<11>2014 AN6-17 N/A (2) N/A X X X X N/A N/A N/A (2) (2) (2) N/A N/A N/A X X X X X 061183 068063 NAS1306-22D X X X X X X X X X X X X X X X C62032 N/A 65700 N/A X X X X X X C62032-1 N/A 65700 N/A X X X X X X C62032-2 N/A 65700 N/A X X X X X X C62032-10 061184 N/A N/A 65700 65700 N/A N/A X X X X X X X X X X X X 061184-1 N/A 65700 N/A X 65700 N/A X X N/A N/A 65700 65700 N/A NIA X X X 068695 C61453 X X X X X N/A X X X X 068076 X X X X X (1) C61453-1 N/A 65700 N/A X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X C61453-15 N/A 65700 N/A C61453-20 N/A 65700 N/A C61453-40 N/A 65700 N/A C61453-41 N/A 65700 N/A X X X X C61453-205 N/A 65700 N/A X X 16:42 Sep 17, 2018 Jkt 244001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4725 E:\FR\FM\18SER1.SGM 18SER1 ER18SE18.002</GPH> ATA32-20-00 NOSE LANDING GEAR BARREL ASSEMBLY (FIG.07) (1) Limitation applicable to WV01 & WV03 only. (2) Part must be replaced by a new one every time it is removed from the barrel. (3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut's removal and reinstallation are performed on the same pin and neither the pin nor the nut accumulates time in service during the period between the removal and reinstallation. N/A (2) N/A X X X X X 068062 X End fitting pin nut (2) N/A X X X X X X MS17825-6 N/A 47052 Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations SAFE LIFE LIMITS (.,.) Part Name Turning tube Part Number FH LOG Cal B2-1A B2-1C B2K-3C B2-20x 82-320 C59050-30 N/A 24000 N/A X X X C59050-40 N/A 24000 N/A X X X C59050-50 N/A 65700 N/A X N/A 65700 N/A X X X X C59050-60 C59050 N/A 24000 N/A X X(1) C59050-2 N/A 24000 N/A X X(1) C59050-3 Torque link pin (Upper & Lower) Torque Links (Upper & Lower) Torque link medium pin Affected Model(s) 24000 24000 N/A N/A X C59050-4 NIA N/A X(1) X C59050-20 N/A 24000 N/A X X X C59050-28 N/A 24000 N/A X X(1) C62223-1 N/A 65700 N/A X C62223-15 N/A 65700 N/A C62223-20 N/A 65700 N/A C59562-2 N/A 65700 N/A X X X X X X X C59562-3 N/A 65700 N/A X X X X X X B4-2C 84-2xx B4-1xx C4-203 F4-203 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X C62041-1 N/A 65700 N/A C62041-15 N/A 65700 N/A C62041-20 N/A 65700 N/A C62041-200 N/A 65700 N/A X X X X X X 053431 N/A 65700 N/A X X X X X X X X X 053431-20 N/A 65700 N/A X X X X X A X X X X C59562-4 N/A 65700 N/A C59562-20 N/A 65700 N/A ~ SL40110P lA X X X SHOCK ABSORBER ASSEMBLY C62270 .. C62034-1 N/A 65700 N/A C62034-10 NIA 65700 C68534 N/A I daltland on DSKBBV9HB2PROD with RULES Upper cam VerDate Sep<11>2014 16:42 Sep 17, 2018 Jkt 244001 ~ PO 00000 X X X X X X X X X X X NIA X X X X X X 65700 N/A X X X X X X Frm 00026 Fmt 4700 ,. TJ Sfmt 4725 E:\FR\FM\18SER1.SGM 18SER1 ER18SE18.003</GPH> (1) Limitation applicable to WV01 & WV03 only. (2) Limitation applicable to WV 00 only. (3) Limitation applicable to WV 08 only. (4) Part must be replaced by a new one every time it is removed from the sliding rod. (5) Part must be replaced by a new one every time it is removed from the upper rod. Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations (h) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. daltland on DSKBBV9HB2PROD with RULES (i) Terminating Action for AD 2014–16–13 Accomplishing the actions required by this AD terminates all requirements of AD 2014– 16–13. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International 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 VerDate Sep<11>2014 16:42 Sep 17, 2018 Jkt 244001 directly to the International Section, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA– authorized signature. http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0390. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3225. (l) Material Incorporated by Reference None. Issued in Des Moines, Washington, on August 24, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–19854 Filed 9–17–18; 8:45 am] BILLING CODE 4910–13–P (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0145, dated August 31, 2017, for related information. This MCAI may be found in the AD docket on the internet at PO 00000 Frm 00027 Fmt 4700 Sfmt 9990 E:\FR\FM\18SER1.SGM 18SER1 ER18SE18.004</GPH> BILLING CODE 4910–13–P 47053

Agencies

[Federal Register Volume 83, Number 181 (Tuesday, September 18, 2018)]
[Rules and Regulations]
[Pages 47047-47053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19854]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0390; Product Identifier 2017-NM-130-AD; Amendment 
39-19397; AD 2018-18-18]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A300 series airplanes. This AD was prompted by a 
revision of an airworthiness limitation items (ALI) document. This AD 
requires revising the maintenance or inspection program, as applicable, 
to incorporate the specified maintenance requirements and airworthiness 
limitations. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective October 23, 2018.

ADDRESSES:

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-2018-
0390; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

SUPPLEMENTARY INFORMATION: 

[[Page 47048]]

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus SAS Model A300 
series airplanes. The NPRM published in the Federal Register on May 11, 
2018 (83 FR 21955). The NPRM was prompted by a revision of an ALI 
document. The NPRM proposed to require revising the maintenance or 
inspection program, as applicable, to incorporate the specified 
maintenance requirements and airworthiness limitations.
    We are issuing this AD to address the reduced structural integrity 
of the airplane and possible loss of controllability of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0145, dated August 31, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A300 series 
airplanes. The MCAI states:

    Some airworthiness limitations previously defined in A300 ALS 
[Airworthiness Limitations Section] Part 1 have been removed from 
that document and should normally be included in an ALS Part 4. 
Airbus does not plan to issue an ALS Part 4 for A300 aeroplanes.
    Nevertheless, failure to comply with these airworthiness 
limitations could result in an unsafe condition.
    For the reason described above, it has been decided to require 
the application of these airworthiness limitations through a 
separate AD.
    Previously, EASA issued AD 2013-0210 [which corresponds to FAA 
AD 2014-16-13, Amendment 39-17937 (79 FR 51083, August 27, 2014) 
(``AD 2014-16-13'')] to require implementation of airworthiness 
limitations applicable to main landing gear (MLG) barrel assembly, 
retraction actuator assembly, linkage assembly and flanged duct, 
which were previously defined in Revision 00 of A300 ALS Part 1 but 
removed from Revision 01 of A300 ALS Part 1, adding those limits as 
an Appendix to the AD.
    Since EASA AD 2013-0210 was issued, improvement of safe life 
component selection resulted, among others, in removal of 15 nose 
landing gear (NLG) parts from Revision 02 of A300 ALS Part 1.
    Consequently, this [EASA] AD retains the requirements of EASA AD 
2013-0210, which is superseded, and requires, in addition to the 
implementation of airworthiness limitations already contained in 
EASA AD 2013-0210, the implementation of airworthiness limitations 
applicable to NLG barrel assembly and shock absorber assembly, 
previously contained in Revision 01 of A300 ALS Part 1, as specified 
in Appendix 1 of this AD.

    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-2018-
0390.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comment received on the 
NPRM and the FAA's response to the comment.

Request To Supersede AD 2014-16-13

    Airbus questioned the need to keep AD 2014-16-13 and whether the 
proposed AD should instead supersede AD 2014-16-13. Airbus noted that 
the proposed AD lists all of the ALIs in EASA AD 2017-0145, dated 
August 31, 2017, not just the ALIs that have been updated since we 
issued AD 2014-16-13. We infer that Airbus wanted the proposed AD 
changed to a supersedure AD.
    We disagree with the request to change this AD to a supersedure AD. 
To address the unsafe condition, we chose to match EASA AD 2017-0145, 
dated August 31, 2017, and include the same ALIs. Because 
accomplishment of the requirements of this AD terminates all 
requirements of AD 2014-16-13, a supersedure is not necessary. We have 
not changed this AD in this regard.

Request To Release Related ADs at the Same Time

    Airbus requested that we release this final rule at the same time 
as the following related ADs to provide clarity to operators. All four 
pending ADs are related to the same removal of 15 nose landing gear 
parts from ALS Part 1, on different airplane models.
     Docket No. FAA-2018-0364, Product Identifier 2017-NM-154-
AD (EASA AD 2017-0204, dated October 12, 2017).
     Docket No. FAA-2018-0365, Product Identifier 2017-NM-155-
AD (EASA AD 2017-0203, dated October 12, 2017).
     Docket No. FAA-2018-0396, Product Identifier 2017-NM-156-
AD (EASA AD 2017-0202, dated October 12, 2017).
    We agree with the request insofar as we can control the publication 
schedule. While we cannot ensure that all four will be published on the 
same date, we will coordinate with the Office of the Federal Register 
(OFR) and attempt to issue all four final rules at the same time.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing 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 final 
rule.

Costs of Compliance

    We estimate that this AD affects 5 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:
    We have determined that revising the maintenance or inspection 
program takes an average of 90 work-hours per operator, although we 
recognize that this number may vary from operator to operator. In the 
past, we have estimated that this action takes 1 work-hour per 
airplane. Since operators incorporate maintenance or inspection program 
changes for their affected fleet(s), we have determined that a per-
operator estimate is more accurate than a per-airplane estimate. 
Therefore, we estimate the total cost per operator to be $7,650 (90 
work-hours x $85 per work-hour).

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.
    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

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Compliance and Airworthiness Division, but during this transition 
period, the Executive Director has delegated the authority to issue ADs 
applicable to transport category airplanes and associated appliances to 
the Director of the System Oversight Division.

Regulatory Findings

    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):

2018-18-18 Airbus SAS: Amendment 39-19397; Docket No. FAA-2018-0390; 
Product Identifier 2017-NM-130-AD.

(a) Effective Date

    This AD is effective October 23, 2018.

(b) Affected ADs

    This AD affects AD 2014-16-13, Amendment 39-17937 (79 FR 51083, 
August 27, 2014) (``AD 2014-16-13'').

(c) Applicability

    This AD applies to Airbus SAS Model A300 B2-1A, B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Time Limits/
Maintenance Checks.

(e) Reason

    This AD was prompted by a revision of an airworthiness 
limitation items (ALI) document. We are issuing this AD to prevent 
reduced structural integrity of the airplane and possible loss of 
controllability of the airplane.

(f) Compliance

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

(g) Revision of Maintenance or Inspection Program

    Within 90 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
safe life limits included in figure 1 to paragraph (g) of this AD. 
The initial compliance time for the replacements is prior to the 
applicable life limits specified in figure 1 to paragraph (g) of 
this AD, or within 90 days after the effective date of this AD, 
whichever occurs later. The term ``FH'' in figure 1 to paragraph (g) 
of this AD means total flight hours. The term ``LDG'' in figure 1 to 
paragraph (g) of this AD means total airplane landings.
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(h) No Alternative Actions or Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (g) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (j)(1) of 
this AD.

(i) Terminating Action for AD 2014-16-13

    Accomplishing the actions required by this AD terminates all 
requirements of AD 2014-16-13.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International 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 (k)(2) of this AD. Information 
may be emailed to: [email protected]. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus SAS's EASA Design Organization 
Approval (DOA). If approved by the DOA, the approval must include 
the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0145, dated August 31, 2017, 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-2018-0390.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.

(l) Material Incorporated by Reference

    None.

    Issued in Des Moines, Washington, on August 24, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-19854 Filed 9-17-18; 8:45 am]
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