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CLG that has not exceeded the applicable life (1) Alternative Methods of Compliance Issued in Des Moines, Washington, on limit specified in paragraph (g)(2)(i), (g)(2)(ii), (AMOCs): The Manager, International April 30, 2018. or (g)(2)(iii) of this AD, since first installation Section, Transport Standards Branch, FAA, Dionne Palermo, on an airplane. has the authority to approve AMOCs for this Acting Director, System Oversight Division, (i) The life limit specified in the applicable AD, if requested using the procedures found Aircraft Certification Service. service information identified in paragraphs in 14 CFR 39.19. In accordance with 14 CFR [FR Doc. 2018–09743 Filed 5–8–18; 8:45 am] (h)(1), (h)(2), and (h)(3) of this AD. 39.19, send your request to your principal (ii) The life limit specified in Airbus A330 inspector or local Flight Standards District BILLING CODE 4910–13–P Airworthiness Limitations Section (ALS) Part Office, as appropriate. If sending information 1, ‘‘Safe Life Airworthiness Limitation Items directly to the International Section, send it (SL–ALI),’’ Revision 09, dated September 18, to the attention of the person identified in DEPARTMENT OF TRANSPORTATION 2017, and A330 ALS Part 1, ‘‘Safe Life paragraph (l)(2) of this AD. Information may Airworthiness Limitation Items (SL–ALI),’’ Federal Aviation Administration Variation 9.2, dated November 28, 2017. be emailed to: 9-ANM-116-AMOC- [email protected]. Before using any (iii) The life limit specified in Airbus A340 14 CFR Part 39 Airworthiness Limitations Section (ALS) Part approved AMOC, notify your appropriate 1, ‘‘Safe Life Airworthiness Limitation Items principal inspector, or lacking a principal [Docket No. FAA–2018–0326; Product (SL–ALI),’’ Revision 09, dated September 18, inspector, the manager of the local flight Identifier 2018–CE–006–AD] 2017, and A340 ALS Part 1, ‘‘Safe Life standards district office/certificate holding Airworthiness Limitation Items (SL–ALI),’’ district office. RIN 2120–AA64 Variation 9.2, dated November 28, 2017. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective Airworthiness Directives; SOCATA (h) Identification of Part Number, Serial Airplanes Number, Weight Variant, and Reduced Life actions from a manufacturer, the action must Limit be accomplished using a method approved AGENCY: Federal Aviation by the Manager, International Section, Administration (FAA), Department of Within 3 months after the effective date of Transport Standards Branch, FAA; or the this AD: Identify the part number and serial Transportation (DOT). European Aviation Safety Agency (EASA); or number of each main fitting, bogie beam, and Airbus’s EASA Design Organization ACTION: Notice of proposed rulemaking sliding piston of the MLG, NLG, and CLG (NPRM). installed on the airplane; identify the Approval (DOA). If approved by the DOA, the approval must include the DOA- airplane’s weight variant; and determine the SUMMARY: We propose to supersede applicable reduced life limit; in accordance authorized signature. (3) Required for Compliance (RC): If any Airworthiness Directive (AD) 98–16–03 with the Accomplishment Instructions of the for SOCATA Models TB 9 and TB 10 applicable service information identified in service information contains procedures or paragraph (h)(1), (h)(2), or (h)(3) of this AD. tests that are identified as RC, those airplanes. This proposed AD results A review of airplane maintenance records is procedures and tests must be done to comply from mandatory continuing acceptable for identification of the installed with this AD; any procedures or tests that are airworthiness information (MCAI) main fittings, bogie beams, and sliding not identified as RC are recommended. Those originated by an aviation authority of pistons of the MLG, NLG, and CLG, provided procedures and tests that are not identified another country to identify and correct the part number and serial number of each as RC may be deviated from using accepted an unsafe condition on an aviation component can be conclusively identified by methods in accordance with the operator’s product. The MCAI describes the unsafe that review. maintenance or inspection program without condition as fatigue cracking of the wing (1) Airbus Service Bulletin A330–32–3281, obtaining approval of an AMOC, provided Revision 02, dated June 16, 2017, including front attachments on the wing and the procedures and tests identified as RC can fuselage sides. We are issuing this Appendixes 01 through 06. be done and the airplane can be put back in (2) Airbus Service Bulletin A340–32–4310, proposed AD to require actions to an airworthy condition. Any substitutions or Revision 02, dated June 16, 2017, including address the unsafe condition on these changes to procedures or tests identified as Appendixes 01 through 06. products. (3) Airbus Service Bulletin A340–32–5119, RC require approval of an AMOC. DATES: We must receive comments on Revision 01, dated January 31, 2017, (l) Related Information including Appendixes 01 through 07. this proposed AD by June 25, 2018. (1) Refer to Mandatory Continuing ADDRESSES: You may send comments by (i) Replacement of Affected Parts Airworthiness Information (MCAI) EASA AD 2017–0185, dated September 22, 2017, for any of the following methods: Prior to exceeding the applicable life limit, • Federal eRulemaking Portal: Go to as specified in the applicable service related information. This MCAI may be information identified in paragraph (h)(1), found in the AD docket on the internet at http://www.regulations.gov. Follow the (h)(2), or (h)(3) of this AD, or within 3 http://www.regulations.gov by searching for instructions for submitting comments. months after the effective date of this AD, and locating Docket No. FAA–2018–0395. • Fax: (202) 493–2251. whichever occurs later: Replace each affected (2) For more information about this AD, • Mail: U.S. Department of part (as defined in paragraph (g)(1) of this contact Vladimir Ulyanov, Aerospace Transportation, Docket Operations, M– AD) with a serviceable part (as defined in Engineer, International Section, Transport 30, West Building Ground Floor, Room paragraph (g)(2) of this AD). Standards Branch, FAA, 2200 South 216th W12–140, 1200 New Jersey Avenue SE, (j) Parts Installation Specification St., Des Moines, WA 98198–6547; telephone Washington, DC 20590. and fax 206–231–3229. • Hand Delivery: U.S. Department of As of the effective date of this AD, any (3) For service information identified in affected part (as defined in paragraph (g)(1) Transportation, Docket Operations, M– this AD, contact Airbus SAS, Airworthiness of this AD) may be used as a replacement 30, West Building Ground Floor, Room Office—EAL, 1 Rond Point Maurice Bellonte, part, provided the affected part is also a W12–140, 1200 New Jersey Avenue SE, 31707 Blagnac Cedex, France; telephone +33 serviceable part (as defined in paragraph Washington, DC 20590, between 9 a.m. 5 61 93 36 96; fax +33 5 61 93 45 80; email (g)(2) of this AD), and following installation, and 5 p.m., Monday through Friday, the affected part is replaced prior to [email protected]; internet http://www.airbus.com. You may except Federal holidays. exceeding the applicable life limit as For service information identified in specified in paragraph (g)(2) of this AD. view this service information at the FAA, Transport Standards Branch, 2200 South this proposed AD, contact SOCATA, (k) Other FAA AD Provisions 216th St., Des Moines, WA. For information Direction des services, 65921 Tarbes The following provisions also apply to this on the availability of this material at the Cedex 9, France; phone: +33 (0) 5 62 41 AD: FAA, call 206–231–3195. 73 00; fax: +33 (0) 5 62 41 76 54; email:

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[email protected]; internet: Since we issued AD 98–16–03, FAA’s Determination and Requirements https://www.mysocata.com/login/ SOCATA developed improved repair of the Proposed AD accueil.php. You may review copies of procedures and increased the This product has been approved by the referenced service information at the applicability to include Model TB 200 the aviation authority of another FAA, Policy and Innovation Division, airplanes. country, and is approved for operation 901 Locust, Kansas City, Missouri The European Aviation Safety Agency in the United States. Pursuant to our 64106. For information on the (EASA), which is the Technical Agent bilateral agreement with this State of availability of this material at the FAA, for the Member States of the European Design Authority, they have notified us call (816) 329–4148. Community, has issued EASA AD No. of the unsafe condition described in the Examining the AD Docket 2018–0030, dated January 31, 2018 MCAI and service information (referred to after this as ‘‘the MCAI’’), to referenced above. We are proposing this You may examine the AD docket on correct an unsafe condition for the AD because we evaluated all the internet at http:// specified products. The MCAI states: information and determined the unsafe www.regulations.gov by searching for condition exists and is likely to exist or and locating Docket No. FAA–2018– During a scheduled maintenance develop on other products of the same 0326; or in person at Docket Operations inspection, cracks were found on the wing type design. between 9 a.m. and 5 p.m., Monday front attachments of a TB 10 aeroplane. This condition, if not detected and through Friday, except Federal holidays. corrected, could affect the structural integrity Costs of Compliance The AD docket contains this proposed of the aeroplane. We estimate that this proposed AD AD, the regulatory evaluation, any Prompted by these findings, SOCATA will affect 126 products of U.S. registry. comments received, and other issued SB 10–081–57 to provide inspection We also estimate that it would take information. The street address for and modification instructions, and DGAC about 3 work-hours per product to Docket Operations (telephone (800) France issued AD 94–264(A), later revised, to comply with the inspection 647–5527) is in the ADDRESSES section. require repetitive inspections of wing front requirements of this proposed AD. We attachments of TB 9 and TB 10 aeroplanes Comments will be available in the AD also estimate that it would take about 25 docket shortly after receipt. (all MSN up to 822 inclusive, with some excluded). That [DGAC France] AD also work-hours per product to comply with FOR FURTHER INFORMATION CONTACT: required installation of reinforcement kits, the replacement/modification (wing and Albert Mercado, Aerospace Engineer, applied as repair (if cracks were found) or as fuselage sides) requirements of this FAA, Small Airplane Standards Branch, modification (if no cracks were found), of the proposed AD. The average labor rate is 901 Locust, Room 301, Kansas City, wing front attachments, on both wing and $85 per work-hour. Required parts Missouri 64106; telephone: (816) 329– fuselage sides, and repetitive replacement of would cost about $3,000 per product. 4119; fax: (816) 329–4090; email: those reinforcements afterwards. Based on these figures, we estimate [email protected]. Since DGAC France AD 94–264(A) R1 was the cost of the proposed AD on U.S. SUPPLEMENTARY INFORMATION: issued, cracks have been found on wing front operators to be $677,880, or $5,380 per attachments, on the wing side, on TB10 product. Comments Invited aeroplanes to which the AD did not apply, i.e. which were not subject to repetitive In addition, we estimate that any We invite you to send any written inspections as required by that [DGAC necessary follow-on actions to replace relevant data, views, or arguments about France] AD. Consequently, SOCATA revised the wing attachment on the wing side, this proposed AD. Send your comments SB 10–081–57 (now at revision (rev) 3), resulting from the repetitive to an address listed under the extending the Applicability to all TB 10 inspections, would take about 9 work- ADDRESSES section. Include ‘‘Docket No. aeroplanes, as well as to TB 200 aeroplanes, hours and require parts costing $3,000, FAA–2018–0326; Product Identifier and improving the repair solution of the wing for a cost of $3,765 per product. We 2018–CE–006–AD’’ at the beginning of front attachment on wing side. have no way of determining the number your comments. We specifically invite For the reason described above, this of products that may need these actions. comments on the overall regulatory, [EASA] AD retains the requirements of DGAC economic, environmental, and energy France AD 94–264(A) R1, which is Authority for This Rulemaking superseded, expands the Applicability to all Title 49 of the United States Code aspects of this proposed AD. We will MSN for TB 9 and TB 10 aeroplanes and consider all comments received by the includes TB 200 aeroplanes, and requires an specifies the FAA’s authority to issue closing date and may amend this improved repair solution of the wing front rules on aviation safety. Subtitle I, proposed AD because of those attachment on wing side. section 106, describes the authority of comments. the FAA Administrator. ‘‘Subtitle VII: We will post all comments we You may examine the MCAI on the Aviation Programs,’’ describes in more receive, without change, to http:// internet at http://www.regulations.gov detail the scope of the Agency’s regulations.gov, including any personal by searching for and locating Docket No. authority. information you provide. We will also FAA–2018–0326. We are issuing this rulemaking under post a report summarizing each Related Service Information Under 1 the authority described in ‘‘Subtitle VII, substantive verbal contact we receive CFR Part 51 Part A, Subpart III, Section 44701: about this proposed AD. General requirements.’’ Under that SOCATA has issued Daher Service section, Congress charges the FAA with Discussion Bulletin SB 10–081, Revision 3, dated promoting safe flight of civil aircraft in We issued AD 98–16–03, Amendment December 2017. The service bulletin air commerce by prescribing regulations 39–10677 (63 FR 40359; July 29, 1998). describes procedures for inspecting the for practices, methods, and procedures That AD required actions intended to front attachments and installing the Administrator finds necessary for address an unsafe condition on modification kits. This service safety in air commerce. This regulation SOCATA Models TB 9 and TB 10 information is reasonably available is within the scope of that authority airplanes and was based on mandatory because the interested parties have because it addresses an unsafe condition continuing airworthiness information access to it through their normal course that is likely to exist or develop on (MCAI) originated by an aviation of business or by the means identified products identified in this rulemaking authority of another country. in the ADDRESSES section of this NPRM. action.

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This AD is issued in accordance with List of Subjects in 14 CFR Part 39 806, 809 through 815, and 820 through 822; authority delegated by the Executive and Air transportation, Aircraft, Aviation Director, Aircraft Certification Service, (2) Group 2 airplanes: Model TB 10, MSN safety, Incorporation by reference, as authorized by FAA Order 8000.51C. 804, 807, 808, 816 through 819, and 823 Safety. In accordance with that order, issuance through 2229; and Model TB 200, all MSNs. of ADs is normally a function of the The Proposed Amendment (d) Subject Compliance and Airworthiness Accordingly, under the authority Air Transport Association of America Division, but during this transition delegated to me by the Administrator, (ATA) Code 57: Wings. period, the Executive Director has the FAA proposes to amend 14 CFR part delegated the authority to issue ADs (e) Reason 39 as follows: applicable to small airplanes, gliders, This AD was prompted by mandatory balloons, airships, domestic business jet PART 39—AIRWORTHINESS continuing airworthiness information (MCAI) transport airplanes, and associated DIRECTIVES originated by an aviation authority of another appliances to the Director of the Policy country to identify and correct an unsafe and Innovation Division. ■ 1. The authority citation for part 39 condition on an aviation product. The MCAI continues to read as follows: describes the unsafe condition as fatigue Regulatory Findings cracking of the wing front attachments on the We determined that this proposed AD Authority: 49 U.S.C. 106(g), 40113, 44701. wing and fuselage sides. We are issuing this AD to prevent fatigue cracking of the wing would not have federalism implications § 39.13 [Amended] under Executive Order 13132. This front attachments, which could lead to ■ 2. The FAA amends § 39.13 by proposed AD would not have a structural failure of the airplane and loss of removing Airworthiness Directive (AD) substantial direct effect on the States, on control. 98–16–03, Amendment 39–10677 (63 the relationship between the national (f) Compliance FR 40359; July 29, 1998), and adding the Government and the States, or on the following new AD: Unless already done, do the following distribution of power and actions listed in paragraphs (g) through (j) of responsibilities among the various SOCATA: Docket No. FAA–2018–0326; this AD. The compliance times of this AD are levels of government. Product Identifier 2018–CE–006–AD. presented in landings instead of hours time- For the reasons discussed above, I (a) Comments Due Date in-service (TIS). If the number of landings is certify this proposed regulation: We must receive comments by June 25, unknown, multiply the number of hours TIS (1) Is not a ‘‘significant regulatory 2018. by 1.5. For the purposes of this AD, ‘‘XX’’ can action’’ under Executive Order 12866, be any numerical value. (b) Affected ADs (2) Is not a ‘‘significant rule’’ under (g) Actions for Airplanes NOT EQUIPPED the DOT Regulatory Policies and This AD replaces AD 98–16–03, With Modification Kit OPT109110XX Procedures (44 FR 11034, February 26, Amendment 39–10677 (63 FR 40359; July 29, (1) Within the compliance time specified 1979), 1998) (‘‘AD 98–16–03’’). in table 1 to paragraph (g)(1) of this AD, do (3) Will not affect intrastate aviation (c) Applicability an initial inspection of the wing front in Alaska, and This AD applies to SOCATA airplanes attachments on the wing side. Inspect (4) Will not have a significant listed in the following groups, certificated in repetitively thereafter at intervals not to economic impact, positive or negative, any category: exceed 3,000 landings. Follow the on a substantial number of small entities (1) Group 1 airplanes: Model TB 9, all Description of Accomplishment Instructions under the criteria of the Regulatory manufacturer serial numbers (MSN); and in SOCATA Daher Service Bulletin SB 10– Flexibility Act. Model TB 10, MSN 001 through 803, 805, 081, Revision 3, December 2017.

(2) If a crack was found during any Daher Service Bulletin SB 10–081, Revision wing side following the Description of inspection required in paragraph (g)(1) of this 3, December 2017. Accomplishment Instructions in SOCATA AD, before further flight, install the (3) Within the compliance time specified Daher Service Bulletin SB 10–081, Revision modification reinforcement kit OPT10911002 in table 2 to paragraph (g)(3) of this AD, 3, December 2017. for the front attachment on the wing side unless already done as corrective action as following the Description of specified in paragraph (g)(2) of this AD, Accomplishment Instructions in SOCATA install the modification reinforcement kit OPT10911002 for the front attachment on the

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(h) Actions for Airplanes EQUIPPED With an initial inspection of the reinforced front Description of Accomplishment Instructions Modification Kit OPT109110XX attachment on the wing side. Inspect in SOCATA Daher Service Bulletin SB 10– (1) Within the compliance time specified repetitively thereafter at intervals not to 081, Revision 3, December 2017. in table 3 to paragraph (h)(1) of this AD, do exceed 3,000 landings. Follow the

(2) Replacing kit OPT109110XX with kit (3) If a crack was found during any (i) Actions for Group 1 Airplanes OPT10911002 on an airplane, at intervals not inspection required in paragraph (h)(1) of (1) Within the compliance time specified to exceed 6,000 landings is acceptable to this AD, before further flight, do the in table 4 to paragraph (i)(1) of this AD, do comply with the inspection requirements of applicable corrective actions following the an initial inspection of the wing front paragraph (h)(1) of this AD for that airplane. Description of Accomplishment Instructions attachments on the fuselage side. Inspect Follow the Description of Accomplishment in SOCATA Daher Service Bulletin SB 10– repetitively thereafter at intervals not to Instructions in SOCATA Daher Service 081, Revision 3, December 2017. exceed 3,000 landings. Follow the Bulletin SB 10–081, Revision 3, December Description of Accomplishment Instructions 2017. in SOCATA Daher Service Bulletin SB 10– 081, Revision 3, December 2017.

(2) If a crack was found during any Daher Service Bulletin SB 10–081, Revision front attachment on fuselage side following inspection required in paragraph (i)(1) of this 3, December 2017. the Description of Accomplishment AD, before further flight, do the applicable (3) Unless already done as corrective action Instructions in SOCATA Daher Service corrective actions following the Description required in paragraph (i)(2) of this AD, Bulletin SB 10–081, Revision 3, December of Accomplishment Instructions in SOCATA within the compliance time specified in table 2017. 5 to paragraph (i)(3) of this AD, reinforce the

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(4) Before or upon accumulating 12,000 Standards Branch, FAA, has the authority to Kansas City, Missouri 64106. For information landings after the reinforcement modification approve AMOCs for this AD, if requested on the availability of this material at the required in paragraph (i)(2) or (3) of this AD, using the procedures found in 14 CFR 39.19. FAA, call (816) 329–4148. replace the reinforced front attachment on Send information to ATTN: Albert Mercado, Issued in Kansas City, Missouri, on April the fuselage side following the Description of Aerospace Engineer, FAA, Small Airplane 30, 2018. Accomplishment Instructions in SOCATA Standards Branch, 901 Locust, Room 301, Daher Service Bulletin SB 10–081, Revision Kansas City, Missouri 64106; telephone: Melvin J. Johnson, 3, December 2017. (816) 329–4119; fax: (816) 329–4090; email: Deputy Director, Policy & Innovation Division, Aircraft Certification Service. (j) Replacement of the Reinforced Front [email protected]. Before using any Attachment approved AMOC on any airplane to which [FR Doc. 2018–09602 Filed 5–8–18; 8:45 am] the AMOC applies, notify your appropriate BILLING CODE 4910–13–P Replacement of the reinforced front principal inspector (PI) in the FAA Flight attachment on the wing side and/or Standards District Office (FSDO), or lacking replacement of the reinforced front a PI, your local FSDO. attachment on the fuselage side, does not (2) Contacting the Manufacturer: For any SECURITIES AND EXCHANGE terminate the inspections required in requirement in this AD to obtain corrective COMMISSION paragraphs (h)(1) and (i)(1) of this AD. After actions from a manufacturer, the action must replacement, the initial and repetitive 17 CFR Part 275 inspection cycle starts over. be accomplished using a method approved by the Manager, Small Airplane Standards [Release No. IA–4889; File No. S7–09–18] (k) Credit for Previous Actions Branch, FAA; or the European Aviation This AD allows credit for the initial Safety Agency (EASA). RIN 3235–AM36 inspection required in paragraphs (g)(1) and (m) Related Information (i)(1) of this AD and any replacement that Proposed Commission Interpretation may have been required based on the initial Refer to MCAI EASA No. 2018–0030, dated Regarding Standard of Conduct for inspection, if done before the effective date January 31, 2018; and Daher Service Bulletin Investment Advisers; Request for of this AD, following Socata Service Bulletin SB 10–081, Revision 3, dated December 2017, Comment on Enhancing Investment No. SB 10–081–57, Revison 1, dated August for related information. You may examine the Adviser Regulation 1996 or Revision 2, dated January 2017. Any MCAI on the internet at http:// inspections or replacements done after the www.regulations.gov by searching for and AGENCY: Securities and Exchange effective date must be done following locating Docket No. FAA–2018–0326. For Commission. service information related to this AD, SOCATA Daher Service Bulletin SB 10–081, ACTION: Proposed interpretation; request Revision 3, December 2017 as specified in contact SOCATA, Direction des services, the Actions and Compliance of this AD. 65921 Tarbes Cedex 9, France; phone: +33 (0) for comment. 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; SUMMARY: (l) Other FAA AD Provisions email: [email protected]; internet: The Securities and Exchange The following provisions also apply to this https://www.mysocata.com/login/ Commission (the ‘‘SEC’’ or the AD: accueil.php. You may review copies of the ‘‘Commission’’) is publishing for (1) Alternative Methods of Compliance referenced service information at the FAA, comment a proposed interpretation of (AMOCs): The Manager, Small Airplane Policy and Innovation Division, 901 Locust, the standard of conduct for investment

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