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(3) For Models 35, 35A, 36, and 36A (j) Alternative Methods of Compliance Issued in Kansas City, Missouri, on August airplanes: Within 24 months after October (AMOCs) 31, 2018. 23, 2018 (the effective date of this AD) or (1) The Manager, Wichita ACO branch, Melvin J. Johnson, within 400 landings after October 23, 2018 FAA, has the authority to approve AMOCs Deputy Director, Policy & Innovation Division, (the effective date of this AD), whichever for this AD, if requested using the procedures Aircraft Certification Service. occurs first, replace the nose roller fitting, nose roller support bracket, and adjacent rib found in 14 CFR 39.19. In accordance with [FR Doc. 2018–19853 Filed 9–17–18; 8:45 am] support structure with replacement parts by 14 CFR 39.19, send your request to your BILLING CODE 4910–13–P following the Accomplishment Instructions principal inspector or local Flight Standards in Bombardier 35/36 SB 35/36–27–50 District Office, as appropriate. If sending Recommended, dated September 11, 2017. information directly to the manager of the DEPARTMENT OF TRANSPORTATION (4) For Models 55, 55B, and 55C airplanes: certification office, send it to the attention of Within 24 months after October 23, 2018 (the the person identified in paragraph (k)(1) of Federal Aviation Administration effective date of this AD) or within 400 this AD. landings after October 23, 2018 (the effective (2) Before using any approved AMOC, 14 CFR Part 39 date of this AD), whichever occurs first, notify your appropriate principal inspector, replace the nose roller fitting, nose roller or lacking a principal inspector, the manager [Docket No. FAA–2018–0390; Product support bracket, and adjacent rib support of the local flight standards district office/ Identifier 2017–NM–130–AD; Amendment structure with replacement parts by certificate holding district office. 39–19397; AD 2018–18–18] following the Accomplishment Instructions in Bombardier SB 55–27–41 (k) Related Information RIN 2120–AA64 Recommended, dated September 11, 2017. For more information about this AD, (5) For Model 60 airplanes: Within 12 Airworthiness Directives; Airbus SAS contact Tara Shawn, Aerospace Engineer, months after October 23, 2018 (the effective Airplanes Wichita ACO Branch, 1801 Airport Road, date of this AD) or within 200 landings after October 23, 2018 (the effective date of this Room 100, Wichita, Kansas 67209; telephone: AGENCY: Federal Aviation AD), whichever occurs first, replace the nose (316) 946–4141; fax: (316) 946–4107; email: Administration (FAA), Department of roller fitting, nose roller support bracket, and [email protected] or [email protected]. Transportation (DOT). adjacent rib support structure with (l) Material Incorporated by Reference ACTION: Final rule. replacement parts by following the (1) The Director of the Federal Register Accomplishment Instructions in Bombardier SUMMARY: We are adopting a new SB 60–27–39 Recommended, approved the incorporation by reference of the service information listed in this airworthiness directive (AD) for all Revision 1, dated January 15, 2018. Airbus SAS Model A300 series (6) For all airplanes: Some compliance paragraph under 5 U.S.C. 552(a) and 1 CFR times in this AD are presented in landings. part 51. airplanes. This AD was prompted by a If you do not keep a record of the total (2) You must use this service information revision of an airworthiness limitation number of landings, then use a 1-to-1 as applicable to do the actions required by items (ALI) document. This AD requires conversion for hours time-in-service (TIS) to this AD, unless the AD specifies otherwise. revising the maintenance or inspection landings. Example: 20 hours TIS = 20 (i) Bombardier Learjet 28/29 Service program, as applicable, to incorporate landings. Bulletin (SB) 28/29–27–31 Recommended, the specified maintenance requirements (7) For Models 31, 31A, 35, 35A, 36, 36A, dated September 11, 2017; and airworthiness limitations. We are 55, 55B, 55C, and 60 airplanes: Although (ii) Bombardier SB 31–27–35 issuing this AD to address the unsafe Paragraph 3.B.(2) of the applicable SB for Recommended, dated September 11, 2017; condition on these products. these models that have modified flap roller (iii) Bombardier /36 SB 35/36 DATES: This AD is effective October 23, assemblies requires the operator to contact –27–50 Recommended, dated September 11, Learjet Inc. for repair instructions, this AD 2017; 2018. requires you do the repair using a method (iv) Bombardier Learjet 55 SB 55–27–41 ADDRESSES: approved by the Manager, Wichita ACO Branch, FAA. For a repair method to be Recommended, dated September 11, 2017; Examining the AD Docket approved by the Manager, Wichita ACO and Branch, as required by this paragraph, the (v) Bombardier Learjet 60 SB 60–27–39 You may examine the AD docket on Manager’s approval letter must specifically Recommended, Revision 1, dated January 15, the internet at http:// refer to this AD. 2018. www.regulations.gov by searching for (3) For service information identified in and locating Docket No. FAA–2018– (h) Credit for Previous Actions this AD, contact Learjet, Inc., One Learjet 0390; or in person at Docket Operations For Model 60 airplanes: This AD allows Way, Wichita, Kansas 67209; telephone: 316– between 9 a.m. and 5 p.m., Monday credit for actions required in paragraph (g)(5) 946–2000; email: ac.ict@ through Friday, except Federal holidays. of this AD if done before the effective date aero.bombardier.com; internet: https:// The AD docket contains this final rule, of this AD following Bombardier Learjet 60 www.bombardier.com. the regulatory evaluation, any SB 60–27–39 Recommended, Basic Issue, (4) You may view this service information dated September 11, 2017. at the FAA, Policy and Innovation Division, comments received, and other information. The address for Docket (i) No Reporting Requirement 901 Locust, Kansas City, Missouri 64106. For information on the availability of this Operations (phone: 800–647–5527) is Although Bombardier Learjet 28/29 SB 28/ material at the FAA, call (816) 329–4148. In U.S. Department of Transportation, 29–27–31 Recommended, dated September addition, you can access this service Docket Operations, M–30, West 11, 2017; Bombardier Learjet 31 SB 31–27– 35 Recommended, dated September 11, 2017; information on the internet at http:// Building Ground Floor, Room W12–140, Bombardier Learjet 35/36 SB 35/36 –27–50 www.regulations.gov by searching for and 1200 New Jersey Avenue SE, Recommended, dated September 11, 2017; locating Docket No. FAA–2017–1078. Washington, DC 20590. Bombardier Learjet 55 SB 55–27–41 (5) You may view this service information FOR FURTHER INFORMATION CONTACT: Dan Recommended, dated September 11, 2017; that is incorporated by reference at the Rodina, Aerospace Engineer, National Archives and Records and Bombardier Learjet 60 SB 60–27–39 International Section, Transport Administration (NARA). For information on Recommended, Revision 1, dated January 15, Standards Branch, FAA, 2200 South 2018, all specify to submit a compliance the availability of this material at NARA, call response form to the manufacturer per 202–741–6030, or go to: http:// 216th St., Des Moines, WA 98198; paragraph 3.E., this AD does not require that www.archives.gov/federal-register/cfr/ibr- telephone and fax 206–231–3225. action. locations.html. SUPPLEMENTARY INFORMATION:

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Discussion You may examine the MCAI in the determined that air safety and the AD docket on the internet at http:// public interest require adopting this We issued a notice of proposed www.regulations.gov by searching for final rule with the changes described rulemaking (NPRM) to amend 14 CFR and locating Docket No. FAA–2018– previously and minor editorial changes. part 39 by adding an AD that would 0390. We have determined that these minor apply to all Airbus SAS Model A300 changes: series airplanes. The NPRM published Comments • Are consistent with the intent that in the Federal Register on May 11, 2018 We gave the public the opportunity to was proposed in the NPRM for (83 FR 21955). The NPRM was participate in developing this final rule. addressing the unsafe condition; and prompted by a revision of an ALI The following presents the comment • Do not add any additional burden document. The NPRM proposed to received on the NPRM and the FAA’s upon the public than was already require revising the maintenance or response to the comment. proposed in the NPRM. inspection program, as applicable, to We also determined that these incorporate the specified maintenance Request To Supersede AD 2014–16–13 changes will not increase the economic requirements and airworthiness Airbus questioned the need to keep burden on any operator or increase the limitations. AD 2014–16–13 and whether the scope of this final rule. We are issuing this AD to address the proposed AD should instead supersede Costs of Compliance reduced structural integrity of the AD 2014–16–13. Airbus noted that the airplane and possible loss of proposed AD lists all of the ALIs in We estimate that this AD affects 5 controllability of the airplane. EASA AD 2017–0145, dated August 31, airplanes of U.S. registry. We estimate the following costs to The European Aviation Safety Agency 2017, not just the ALIs that have been comply with this AD: (EASA), which is the Technical Agent updated since we issued AD 2014–16– We have determined that revising the for the Member States of the European 13. We infer that Airbus wanted the maintenance or inspection program Union, has issued EASA AD 2017–0145, proposed AD changed to a supersedure takes an average of 90 work-hours per dated August 31, 2017 (referred to after AD. operator, although we recognize that this as the Mandatory Continuing We disagree with the request to this number may vary from operator to Airworthiness Information, or ‘‘the change this AD to a supersedure AD. To operator. In the past, we have estimated MCAI’’), to correct an unsafe condition address the unsafe condition, we chose that this action takes 1 work-hour per for all Airbus SAS Model A300 series to match EASA AD 2017–0145, dated airplane. Since operators incorporate airplanes. The MCAI states: August 31, 2017, and include the same ALIs. Because accomplishment of the maintenance or inspection program Some airworthiness limitations previously requirements of this AD terminates all changes for their affected fleet(s), we defined in A300 ALS [Airworthiness requirements of AD 2014–16–13, a have determined that a per-operator Limitations Section] Part 1 have been supersedure is not necessary. We have estimate is more accurate than a per- removed from that document and should airplane estimate. Therefore, we normally be included in an ALS Part 4. not changed this AD in this regard. Airbus does not plan to issue an ALS Part 4 estimate the total cost per operator to be Request To Release Related ADs at the $7,650 (90 work-hours × $85 per work- for A300 aeroplanes. Same Time Nevertheless, failure to comply with these hour). airworthiness limitations could result in an Airbus requested that we release this Authority for This Rulemaking unsafe condition. final rule at the same time as the For the reason described above, it has been following related ADs to provide clarity Title 49 of the United States Code decided to require the application of these to operators. All four pending ADs are specifies the FAA’s authority to issue airworthiness limitations through a separate related to the same removal of 15 nose rules on aviation safety. Subtitle I, AD. section 106, describes the authority of Previously, EASA issued AD 2013–0210 landing gear parts from ALS Part 1, on different airplane models. the FAA Administrator. Subtitle VII: [which corresponds to FAA AD 2014–16–13, • Amendment 39–17937 (79 FR 51083, August Docket No. FAA–2018–0364, Aviation Programs, describes in more 27, 2014) (‘‘AD 2014–16–13’’)] to require Product Identifier 2017–NM–154–AD detail the scope of the Agency’s implementation of airworthiness limitations (EASA AD 2017–0204, dated October authority. applicable to main landing gear (MLG) barrel 12, 2017). We are issuing this rulemaking under assembly, retraction actuator assembly, • Docket No. FAA–2018–0365, the authority described in Subtitle VII, linkage assembly and flanged duct, which Product Identifier 2017–NM–155–AD Part A, Subpart III, Section 44701: were previously defined in Revision 00 of (EASA AD 2017–0203, dated October ‘‘General requirements.’’ Under that A300 ALS Part 1 but removed from Revision 12, 2017). section, Congress charges the FAA with 01 of A300 ALS Part 1, adding those limits • Docket No. FAA–2018–0396, promoting safe flight of civil aircraft in as an Appendix to the AD. air commerce by prescribing regulations Since EASA AD 2013–0210 was issued, Product Identifier 2017–NM–156–AD improvement of safe life component selection (EASA AD 2017–0202, dated October for practices, methods, and procedures resulted, among others, in removal of 15 nose 12, 2017). the Administrator finds necessary for landing gear (NLG) parts from Revision 02 of We agree with the request insofar as safety in air commerce. This regulation A300 ALS Part 1. we can control the publication is within the scope of that authority Consequently, this [EASA] AD retains the schedule. While we cannot ensure that because it addresses an unsafe condition requirements of EASA AD 2013–0210, which all four will be published on the same that is likely to exist or develop on is superseded, and requires, in addition to date, we will coordinate with the Office products identified in this rulemaking the implementation of airworthiness of the Federal Register (OFR) and action. limitations already contained in EASA AD This AD is issued in accordance with 2013–0210, the implementation of attempt to issue all four final rules at the airworthiness limitations applicable to NLG same time. authority delegated by the Executive Director, Aircraft Certification Service, barrel assembly and shock absorber Conclusion assembly, previously contained in Revision as authorized by FAA Order 8000.51C. 01 of A300 ALS Part 1, as specified in We reviewed the relevant data, In accordance with that order, issuance Appendix 1 of this AD. considered the comments received, and of ADs is normally a function of the

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Compliance and Airworthiness List of Subjects in 14 CFR Part 39 2C, B4–103, and B4–203 airplanes, certificated in any category. Division, but during this transition Air transportation, Aircraft, Aviation period, the Executive Director has safety, Incorporation by reference, (d) Subject delegated the authority to issue ADs Safety. Air Transport Association (ATA) of applicable to transport category Adoption of the Amendment America Code 05, Time Limits/Maintenance airplanes and associated appliances to Checks. the Director of the System Oversight Accordingly, under the authority Division. delegated to me by the Administrator, (e) Reason Regulatory Findings the FAA amends 14 CFR part 39 as This AD was prompted by a revision of an follows: airworthiness limitation items (ALI) This AD will not have federalism document. We are issuing this AD to prevent implications under Executive Order PART 39—AIRWORTHINESS reduced structural integrity of the airplane 13132. This AD will not have a DIRECTIVES and possible loss of controllability of the substantial direct effect on the States, on airplane. ■ 1. The authority citation for part 39 the relationship between the national continues to read as follows: (f) Compliance government and the States, or on the Comply with this AD within the Authority: 49 U.S.C. 106(g), 40113, 44701. distribution of power and compliance times specified, unless already responsibilities among the various § 39.13 [Amended] done. levels of government. ■ 2. The FAA amends § 39.13 by adding (g) Revision of Maintenance or Inspection For the reasons discussed above, I the following new airworthiness Program certify that this AD: directive (AD): Within 90 days after the effective date of (1) Is not a ‘‘significant regulatory this AD, revise the maintenance or inspection action’’ under Executive Order 12866, 2018–18–18 Airbus SAS: Amendment 39– 19397; Docket No. FAA–2018–0390; program, as applicable, to incorporate the (2) Is not a ‘‘significant rule’’ under Product Identifier 2017–NM–130–AD. safe life limits included in figure 1 to the DOT Regulatory Policies and paragraph (g) of this AD. The initial (a) Effective Date Procedures (44 FR 11034, February 26, compliance time for the replacements is prior 1979), This AD is effective October 23, 2018. to the applicable life limits specified in figure (3) Will not affect intrastate aviation (b) Affected ADs 1 to paragraph (g) of this AD, or within 90 days after the effective date of this AD, in Alaska, and This AD affects AD 2014–16–13, whichever occurs later. The term ‘‘FH’’ in Amendment 39–17937 (79 FR 51083, August (4) Will not have a significant figure 1 to paragraph (g) of this AD means 27, 2014) (‘‘AD 2014–16–13’’). economic impact, positive or negative, total flight hours. The term ‘‘LDG’’ in figure on a substantial number of small entities (c) Applicability 1 to paragraph (g) of this AD means total under the criteria of the Regulatory This AD applies to Airbus SAS Model airplane landings. Flexibility Act. A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– BILLING CODE 4910–13–P

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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 (*) Affected Model(s) Part Name Part Number B2-1A 82K-3C B4-2C C4-203 FH LOG Cal 82-320 84_2xx B2-1C B2-20x B4-1xx F4-203 ATA 32-1~0 MAIN LANDING GEAR BARREL ASSEMBLY C66277-10 NJA 66600 N/A X X X X C66277-12 NJA 76600 N/A X X X X Stirrup C66277-14 NJA 76600 N/A X X X X 058303-1 N/A 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 Stirrup pin 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 Universal joint 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 Plate (Upper C61637-11 NJA 76600 N/A X X end) C61637-12 N/A 76600 N/A X X C61638-10 N/A 53300 N/A X X Plate (Rear head C61638-11 N/A 53300 N/A X X end) C61638-20 NJA 76600 N/A X X Tie rod C68523-3 NJA 76600 N/A X X 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 34000 N/A X X C69028-4 N/A 34000 N/A X X C69029-1 (1) N/A 32000 N/A X X X X Sliding rod C69029-2 N/A 32000 N/A X X X X C69029-3 N/A 32000 N/A X X X X C69029-4 (2) N/A 22000 N/A X X X X C67078 NJA 33000 N/A X X X X Piston C67078-1 N/A 33000 N/A X X X X C61342-4 NJA 36700 N/A X X End fitting C66510-4 NJA 32000 N/A X X X X

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LINKAGE ASSEMBLY Upper C61505 NIA 76600 N/A X X multiple link C61505-1 NIA 76600 N/A X 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 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. End fitting 068062 N/A (2) N/A X X X X X X pin nut MS17825-6 N/A (2) N/A X X X X X X AN6-17 N/A (2) N/A X X X X X X 061183 N/A (2) N/A X X X X X X End fitting pin 068063 N/A (2) N/A X X X X X X NAS1306-22D N/A (2) N/A 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 End fitting C62032-10 N/A 65700 N/A X X X X X X 061184 N/A 65700 N/A X X X X X X 061184-1 N/A 65700 N/A X X X X X X 068076 N/A 65700 N/A X X X X X X 068695 N/A 65700 N/A X X X X X X C61453 N/A 65700 NIA X X (1) C61453-1 N/A 65700 N/A X X X X X X C61453-15 N/A 65700 N/A X X X X X X Rack C61453-20 N/A 65700 N/A X X X X X X C61453-40 N/A 65700 N/A X X X X X X C61453-41 N/A 65700 N/A X X X X X X C61453-205 N/A 65700 N/A X X X X X X

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SAFE LIFE LIMITS (.,.) Affected Model(s) Part Name Part Number B2-1A B2K-3C B4-2C C4-203 FH LOG Cal 82-320 84-2xx B2-1C B2-20x B4-1xx F4-203 C59050-30 N/A 24000 N/A X X X X X X C59050-40 N/A 24000 N/A X X X X X X C59050-50 N/A 65700 N/A X X X X X X C59050-60 N/A 65700 N/A X X X X X X C59050 N/A 24000 N/A X X(1) Turning tube C59050-2 N/A 24000 N/A X X(1) X X X X C59050-3 NIA 24000 N/A X X(1) C59050-4 N/A 24000 N/A X X X X X X C59050-20 N/A 24000 N/A X X X X X X C59050-28 N/A 24000 N/A X X(1) X X X X C62223-1 N/A 65700 N/A X X X X X X Torque link pin (Upper & Lower) C62223-15 N/A 65700 N/A X X X X X X C62223-20 N/A 65700 N/A X X X X X X C59562-2 N/A 65700 N/A X X X X X X Torque Links C59562-3 N/A 65700 N/A X X X X (Upper & Lower) C59562-4 N/A 65700 N/A X X X X X X C59562-20 N/A 65700 N/A X X X X X X C62041-1 N/A 65700 N/A X X X X X X C62041-15 N/A 65700 N/A X X X X X X Torque link C62041-20 N/A 65700 N/A X X X X X X medium pin 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 053431-20 N/A 65700 N/A X X X X X X

~ lA SL40110P A X X X X

SHOCK ABSORBER ASSEMBLY (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.

C62270 ~ ,. TJ X X X X X I .. C62034-1 N/A 65700 N/A X X X X X X Upper cam C62034-10 NIA 65700 NIA X X X X X X C68534 N/A 65700 N/A X X X X X X

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BILLING CODE 4910–13–P directly to the International Section, send it http://www.regulations.gov by searching for (h) No Alternative Actions or Intervals to the attention of the person identified in and locating Docket No. FAA–2018–0390. paragraph (k)(2) of this AD. Information may (2) For more information about this AD, After the maintenance or inspection be emailed to: 9-ANM-116-AMOC- program has been revised as required by contact Dan Rodina, Aerospace Engineer, paragraph (g) of this AD, no alternative [email protected]. Before using any International Section, Transport Standards actions (e.g., inspections) or intervals may be approved AMOC, notify your appropriate Branch, FAA, 2200 South 216th St., Des used unless the actions or intervals are principal inspector, or lacking a principal Moines, WA 98198; telephone and fax 206– approved as an alternative method of inspector, the manager of the local flight 231–3225. compliance (AMOC) in accordance with the standards district office/certificate holding procedures specified in paragraph (j)(1) of district office. (l) Material Incorporated by Reference this AD. (2) Contacting the Manufacturer: For any None. requirement in this AD to obtain corrective (i) Terminating Action for AD 2014–16–13 Issued in Des Moines, Washington, on actions from a manufacturer, the action must Accomplishing the actions required by this be accomplished using a method approved August 24, 2018. AD terminates all requirements of AD 2014– by the Manager, International Section, James Cashdollar, 16–13. Transport Standards Branch, FAA; or the Acting Director, System Oversight Division, (j) Other FAA AD Provisions European Aviation Safety Agency (EASA); or Aircraft Certification Service. The following provisions also apply to this Airbus SAS’s EASA Design Organization [FR Doc. 2018–19854 Filed 9–17–18; 8:45 am] Approval (DOA). If approved by the DOA, AD: BILLING CODE 4910–13–P (1) Alternative Methods of Compliance the approval must include the DOA– (AMOCs): The Manager, International authorized signature. Section, Transport Standards Branch, FAA, (k) Related Information has the authority to approve AMOCs for this AD, if requested using the procedures found (1) Refer to Mandatory Continuing in 14 CFR 39.19. In accordance with 14 CFR Airworthiness Information (MCAI) EASA AD 39.19, send your request to your principal 2017–0145, dated August 31, 2017, for inspector or local Flight Standards District related information. This MCAI may be Office, as appropriate. If sending information found in the AD docket on the internet at

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