Airworthiness Directives; SOCATA Airplanes, 21199-21203 [2018-09602]

Download as PDF Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules CLG that has not exceeded the applicable life limit specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD, since first installation on an airplane. (i) The life limit specified in the applicable service information identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (ii) The life limit specified in Airbus A330 Airworthiness Limitations Section (ALS) Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Revision 09, dated September 18, 2017, and A330 ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Variation 9.2, dated November 28, 2017. (iii) The life limit specified in Airbus A340 Airworthiness Limitations Section (ALS) Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Revision 09, dated September 18, 2017, and A340 ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Variation 9.2, dated November 28, 2017. (h) Identification of Part Number, Serial Number, Weight Variant, and Reduced Life Limit Within 3 months after the effective date of this AD: Identify the part number and serial number of each main fitting, bogie beam, and sliding piston of the MLG, NLG, and CLG installed on the airplane; identify the airplane’s weight variant; and determine the applicable reduced life limit; in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. A review of airplane maintenance records is acceptable for identification of the installed main fittings, bogie beams, and sliding pistons of the MLG, NLG, and CLG, provided the part number and serial number of each component can be conclusively identified by that review. (1) Airbus Service Bulletin A330–32–3281, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. (2) Airbus Service Bulletin A340–32–4310, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. (3) Airbus Service Bulletin A340–32–5119, Revision 01, dated January 31, 2017, including Appendixes 01 through 07. amozie on DSK3GDR082PROD with PROPOSALS (i) Replacement of Affected Parts Prior to exceeding the applicable life limit, as specified in the applicable service information identified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, or within 3 months after the effective date of this AD, whichever occurs later: Replace each affected part (as defined in paragraph (g)(1) of this AD) with a serviceable part (as defined in paragraph (g)(2) of this AD). (j) Parts Installation Specification As of the effective date of this AD, any affected part (as defined in paragraph (g)(1) of this AD) may be used as a replacement part, provided the affected part is also a serviceable part (as defined in paragraph (g)(2) of this AD), and following installation, the affected part is replaced prior to exceeding the applicable life limit as specified in paragraph (g)(2) of this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 (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 (l)(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’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0185, dated September 22, 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–2018–0395. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198–6547; telephone and fax 206–231–3229. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. PO 00000 Frm 00012 Fmt 4702 Issued in Des Moines, Washington, on April 30, 2018. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09743 Filed 5–8–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0326; Product Identifier 2018–CE–006–AD] RIN 2120–AA64 Airworthiness Directives; SOCATA Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 98–16–03 for SOCATA Models TB 9 and TB 10 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue cracking of the wing front attachments on the wing and fuselage sides. We are issuing this proposed AD to require actions to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by June 25, 2018. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone: +33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email: DATES: (l) Related Information Sfmt 4702 21199 E:\FR\FM\09MYP1.SGM 09MYP1 21200 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules info@socata.daher.com; internet: https://www.mysocata.com/login/ accueil.php. You may review copies of the referenced 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. 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– 0326; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090; email: albert.mercado@faa.gov. SUPPLEMENTARY INFORMATION: amozie on DSK3GDR082PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–0326; Product Identifier 2018–CE–006–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 98–16–03, Amendment 39–10677 (63 FR 40359; July 29, 1998). That AD required actions intended to address an unsafe condition on SOCATA Models TB 9 and TB 10 airplanes and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 Since we issued AD 98–16–03, SOCATA developed improved repair procedures and increased the applicability to include Model TB 200 airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2018–0030, dated January 31, 2018 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During a scheduled maintenance inspection, cracks were found on the wing front attachments of a TB 10 aeroplane. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. Prompted by these findings, SOCATA issued SB 10–081–57 to provide inspection and modification instructions, and DGAC France issued AD 94–264(A), later revised, to require repetitive inspections of wing front attachments of TB 9 and TB 10 aeroplanes (all MSN up to 822 inclusive, with some excluded). That [DGAC France] AD also required installation of reinforcement kits, applied as repair (if cracks were found) or as modification (if no cracks were found), of the wing front attachments, on both wing and fuselage sides, and repetitive replacement of those reinforcements afterwards. Since DGAC France AD 94–264(A) R1 was issued, cracks have been found on wing front attachments, on the wing side, on TB10 aeroplanes to which the AD did not apply, i.e. which were not subject to repetitive inspections as required by that [DGAC France] AD. Consequently, SOCATA revised SB 10–081–57 (now at revision (rev) 3), extending the Applicability to all TB 10 aeroplanes, as well as to TB 200 aeroplanes, and improving the repair solution of the wing front attachment on wing side. For the reason described above, this [EASA] AD retains the requirements of DGAC France AD 94–264(A) R1, which is superseded, expands the Applicability to all MSN for TB 9 and TB 10 aeroplanes and includes TB 200 aeroplanes, and requires an improved repair solution of the wing front attachment on wing side. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0326. Related Service Information Under 1 CFR Part 51 SOCATA has issued Daher Service Bulletin SB 10–081, Revision 3, dated December 2017. The service bulletin describes procedures for inspecting the front attachments and installing modification kits. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD will affect 126 products of U.S. registry. We also estimate that it would take about 3 work-hours per product to comply with the inspection requirements of this proposed AD. We also estimate that it would take about 25 work-hours per product to comply with the replacement/modification (wing and fuselage sides) requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $3,000 per product. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $677,880, or $5,380 per product. In addition, we estimate that any necessary follow-on actions to replace the wing attachment on the wing side, resulting from the repetitive inspections, would take about 9 workhours and require parts costing $3,000, for a cost of $3,765 per product. We have no way of determining the number of products that may need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. E:\FR\FM\09MYP1.SGM 09MYP1 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules Regulatory Findings amozie on DSK3GDR082PROD with PROPOSALS We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (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. (2) If a crack was found during any inspection required in paragraph (g)(1) of this AD, before further flight, install the modification reinforcement kit OPT10911002 for the front attachment on the wing side following the Description of Accomplishment Instructions in SOCATA VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 806, 809 through 815, and 820 through 822; and (2) Group 2 airplanes: Model TB 10, MSN 804, 807, 808, 816 through 819, and 823 through 2229; and Model TB 200, all MSNs. The Proposed Amendment (d) Subject Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Air Transport Association of America (ATA) Code 57: Wings. List of Subjects in 14 CFR Part 39 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 removing Airworthiness Directive (AD) 98–16–03, Amendment 39–10677 (63 FR 40359; July 29, 1998), and adding the following new AD: ■ SOCATA: Docket No. FAA–2018–0326; Product Identifier 2018–CE–006–AD. (a) Comments Due Date We must receive comments by June 25, 2018. (b) Affected ADs This AD replaces AD 98–16–03, Amendment 39–10677 (63 FR 40359; July 29, 1998) (‘‘AD 98–16–03’’). (c) Applicability This AD applies to SOCATA airplanes listed in the following groups, certificated in any category: (1) Group 1 airplanes: Model TB 9, all manufacturer serial numbers (MSN); and Model TB 10, MSN 001 through 803, 805, Daher Service Bulletin SB 10–081, Revision 3, December 2017. (3) Within the compliance time specified in table 2 to paragraph (g)(3) of this AD, unless already done as corrective action as specified in paragraph (g)(2) of this AD, install the modification reinforcement kit OPT10911002 for the front attachment on the PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue cracking of the wing front attachments on the wing and fuselage sides. We are issuing this AD to prevent fatigue cracking of the wing front attachments, which could lead to structural failure of the airplane and loss of control. (f) Compliance Unless already done, do the following actions listed in paragraphs (g) through (j) of this AD. The compliance times of this AD are presented in landings instead of hours timein-service (TIS). If the number of landings is unknown, multiply the number of hours TIS by 1.5. For the purposes of this AD, ‘‘XX’’ can be any numerical value. (g) Actions for Airplanes NOT EQUIPPED With Modification Kit OPT109110XX (1) Within the compliance time specified in table 1 to paragraph (g)(1) of this AD, do an initial inspection of the wing front attachments on the wing side. Inspect repetitively thereafter at intervals not to exceed 3,000 landings. Follow the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10– 081, Revision 3, December 2017. wing side following the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10–081, Revision 3, December 2017. E:\FR\FM\09MYP1.SGM 09MYP1 EP09MY18.019</GPH> This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division. 21201 21202 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules an initial inspection of the reinforced front attachment on the wing side. Inspect repetitively thereafter at intervals not to exceed 3,000 landings. Follow the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10– 081, Revision 3, December 2017. (2) Replacing kit OPT109110XX with kit OPT10911002 on an airplane, at intervals not to exceed 6,000 landings is acceptable to comply with the inspection requirements of paragraph (h)(1) of this AD for that airplane. Follow the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10–081, Revision 3, December 2017. (3) If a crack was found during any inspection required in paragraph (h)(1) of this AD, before further flight, do the applicable corrective actions following the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10– 081, Revision 3, December 2017. (i) Actions for Group 1 Airplanes (2) If a crack was found during any inspection required in paragraph (i)(1) of this AD, before further flight, do the applicable corrective actions following the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10–081, Revision 3, December 2017. (3) Unless already done as corrective action required in paragraph (i)(2) of this AD, within the compliance time specified in table 5 to paragraph (i)(3) of this AD, reinforce the front attachment on fuselage side following the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10–081, Revision 3, December 2017. VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 (1) Within the compliance time specified in table 4 to paragraph (i)(1) of this AD, do an initial inspection of the wing front attachments on the fuselage side. Inspect repetitively thereafter at intervals not to exceed 3,000 landings. Follow the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10– 081, Revision 3, December 2017. E:\FR\FM\09MYP1.SGM 09MYP1 EP09MY18.022</GPH> amozie on DSK3GDR082PROD with PROPOSALS (1) Within the compliance time specified in table 3 to paragraph (h)(1) of this AD, do EP09MY18.020</GPH> EP09MY18.021</GPH> (h) Actions for Airplanes EQUIPPED With Modification Kit OPT109110XX Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules amozie on DSK3GDR082PROD with PROPOSALS (j) Replacement of the Reinforced Front Attachment Replacement of the reinforced front attachment on the wing side and/or replacement of the reinforced front attachment on the fuselage side, does not terminate the inspections required in paragraphs (h)(1) and (i)(1) of this AD. After replacement, the initial and repetitive inspection cycle starts over. (k) Credit for Previous Actions This AD allows credit for the initial inspection required in paragraphs (g)(1) and (i)(1) of this AD and any replacement that may have been required based on the initial inspection, if done before the effective date of this AD, following Socata Service Bulletin No. SB 10–081–57, Revison 1, dated August 1996 or Revision 2, dated January 2017. Any inspections or replacements done after the effective date must be done following SOCATA Daher Service Bulletin SB 10–081, Revision 3, December 2017 as specified in the Actions and Compliance of this AD. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; fax: (816) 329–4090; email: albert.mercado@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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, Small Airplane Standards Branch, FAA; or the European Aviation Safety Agency (EASA). Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (m) Related Information Refer to MCAI EASA No. 2018–0030, dated January 31, 2018; and Daher Service Bulletin SB 10–081, Revision 3, dated December 2017, for related information. You may examine the MCAI on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0326. For service information related to this AD, contact SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone: +33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email: info@socata.daher.com; internet: https://www.mysocata.com/login/ accueil.php. You may review copies of the referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Proposed Commission Interpretation Regarding Standard of Conduct for Investment Advisers; Request for Comment on Enhancing Investment Adviser Regulation PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Issued in Kansas City, Missouri, on April 30, 2018. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–09602 Filed 5–8–18; 8:45 am] BILLING CODE 4910–13–P SECURITIES AND EXCHANGE COMMISSION 17 CFR Part 275 [Release No. IA–4889; File No. S7–09–18] RIN 3235–AM36 Securities and Exchange Commission. ACTION: Proposed interpretation; request for comment. AGENCY: The Securities and Exchange Commission (the ‘‘SEC’’ or the ‘‘Commission’’) is publishing for comment a proposed interpretation of the standard of conduct for investment SUMMARY: E:\FR\FM\09MYP1.SGM 09MYP1 EP09MY18.023</GPH> (4) Before or upon accumulating 12,000 landings after the reinforcement modification required in paragraph (i)(2) or (3) of this AD, replace the reinforced front attachment on the fuselage side following the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10–081, Revision 3, December 2017. 21203

Agencies

[Federal Register Volume 83, Number 90 (Wednesday, May 9, 2018)]
[Proposed Rules]
[Pages 21199-21203]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09602]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD]
RIN 2120-AA64


Airworthiness Directives; SOCATA Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-16-03 
for SOCATA Models TB 9 and TB 10 airplanes. This proposed AD results 
from mandatory continuing airworthiness information (MCAI) originated 
by an aviation authority of another country to identify and correct an 
unsafe condition on an aviation product. The MCAI describes the unsafe 
condition as fatigue cracking of the wing front attachments on the wing 
and fuselage sides. We are issuing this proposed AD to require actions 
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 25, 2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone: 
+33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email:

[[Page 21200]]

[email protected]; internet: https://www.mysocata.com/login/accueil.php. You may review copies of the referenced 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.

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-
0326; 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 proposed AD, the regulatory evaluation, any comments received, and 
other information. The street address for Docket Operations (telephone 
(800) 647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, 
FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas 
City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; 
email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0326; 
Product Identifier 2018-CE-006-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 98-16-03, Amendment 39-10677 (63 FR 40359; July 29, 
1998). That AD required actions intended to address an unsafe condition 
on SOCATA Models TB 9 and TB 10 airplanes and was based on mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country.
    Since we issued AD 98-16-03, SOCATA developed improved repair 
procedures and increased the applicability to include Model TB 200 
airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No. 2018-0030, dated January 31, 2018 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During a scheduled maintenance inspection, cracks were found on 
the wing front attachments of a TB 10 aeroplane.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Prompted by these findings, SOCATA issued SB 10-081-57 to 
provide inspection and modification instructions, and DGAC France 
issued AD 94-264(A), later revised, to require repetitive 
inspections of wing front attachments of TB 9 and TB 10 aeroplanes 
(all MSN up to 822 inclusive, with some excluded). That [DGAC 
France] AD also required installation of reinforcement kits, applied 
as repair (if cracks were found) or as modification (if no cracks 
were found), of the wing front attachments, on both wing and 
fuselage sides, and repetitive replacement of those reinforcements 
afterwards.
    Since DGAC France AD 94-264(A) R1 was issued, cracks have been 
found on wing front attachments, on the wing side, on TB10 
aeroplanes to which the AD did not apply, i.e. which were not 
subject to repetitive inspections as required by that [DGAC France] 
AD. Consequently, SOCATA revised SB 10-081-57 (now at revision (rev) 
3), extending the Applicability to all TB 10 aeroplanes, as well as 
to TB 200 aeroplanes, and improving the repair solution of the wing 
front attachment on wing side.
    For the reason described above, this [EASA] AD retains the 
requirements of DGAC France AD 94-264(A) R1, which is superseded, 
expands the Applicability to all MSN for TB 9 and TB 10 aeroplanes 
and includes TB 200 aeroplanes, and requires an improved repair 
solution of the wing front attachment on wing side.

    You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0326.

Related Service Information Under 1 CFR Part 51

    SOCATA has issued Daher Service Bulletin SB 10-081, Revision 3, 
dated December 2017. The service bulletin describes procedures for 
inspecting the front attachments and installing modification kits. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section of this NPRM.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Costs of Compliance

    We estimate that this proposed AD will affect 126 products of U.S. 
registry. We also estimate that it would take about 3 work-hours per 
product to comply with the inspection requirements of this proposed AD. 
We also estimate that it would take about 25 work-hours per product to 
comply with the replacement/modification (wing and fuselage sides) 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $3,000 per product.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $677,880, or $5,380 per product.
    In addition, we estimate that any necessary follow-on actions to 
replace the wing attachment on the wing side, resulting from the 
repetitive inspections, would take about 9 work-hours and require parts 
costing $3,000, for a cost of $3,765 per product. We have no way of 
determining the number of products that may need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

[[Page 21201]]

    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
98-16-03, Amendment 39-10677 (63 FR 40359; July 29, 1998), and adding 
the following new AD:

SOCATA: Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD.

(a) Comments Due Date

    We must receive comments by June 25, 2018.

(b) Affected ADs

    This AD replaces AD 98-16-03, Amendment 39-10677 (63 FR 40359; 
July 29, 1998) (``AD 98-16-03'').

(c) Applicability

    This AD applies to SOCATA airplanes listed in the following 
groups, certificated in any category:
    (1) Group 1 airplanes: Model TB 9, all manufacturer serial 
numbers (MSN); and Model TB 10, MSN 001 through 803, 805, 806, 809 
through 815, and 820 through 822; and
    (2) Group 2 airplanes: Model TB 10, MSN 804, 807, 808, 816 
through 819, and 823 through 2229; and Model TB 200, all MSNs.

(d) Subject

    Air Transport Association of America (ATA) Code 57: Wings.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as fatigue cracking 
of the wing front attachments on the wing and fuselage sides. We are 
issuing this AD to prevent fatigue cracking of the wing front 
attachments, which could lead to structural failure of the airplane 
and loss of control.

(f) Compliance

    Unless already done, do the following actions listed in 
paragraphs (g) through (j) of this AD. The compliance times of this 
AD are presented in landings instead of hours time-in-service (TIS). 
If the number of landings is unknown, multiply the number of hours 
TIS by 1.5. For the purposes of this AD, ``XX'' can be any numerical 
value.

(g) Actions for Airplanes NOT EQUIPPED With Modification Kit 
OPT109110XX

    (1) Within the compliance time specified in table 1 to paragraph 
(g)(1) of this AD, do an initial inspection of the wing front 
attachments on the wing side. Inspect repetitively thereafter at 
intervals not to exceed 3,000 landings. Follow the Description of 
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
[GRAPHIC] [TIFF OMITTED] TP09MY18.019

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

[[Page 21202]]

[GRAPHIC] [TIFF OMITTED] TP09MY18.020

(h) Actions for Airplanes EQUIPPED With Modification Kit OPT109110XX

    (1) Within the compliance time specified in table 3 to paragraph 
(h)(1) of this AD, do an initial inspection of the reinforced front 
attachment on the wing side. Inspect repetitively thereafter at 
intervals not to exceed 3,000 landings. Follow the Description of 
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
[GRAPHIC] [TIFF OMITTED] TP09MY18.021

    (2) Replacing kit OPT109110XX with kit OPT10911002 on an 
airplane, at intervals not to exceed 6,000 landings is acceptable to 
comply with the inspection requirements of paragraph (h)(1) of this 
AD for that airplane. Follow the Description of Accomplishment 
Instructions in SOCATA Daher Service Bulletin SB 10-081, Revision 3, 
December 2017.
    (3) If a crack was found during any inspection required in 
paragraph (h)(1) of this AD, before further flight, do the 
applicable corrective actions following the Description of 
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.

(i) Actions for Group 1 Airplanes

    (1) Within the compliance time specified in table 4 to paragraph 
(i)(1) of this AD, do an initial inspection of the wing front 
attachments on the fuselage side. Inspect repetitively thereafter at 
intervals not to exceed 3,000 landings. Follow the Description of 
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
[GRAPHIC] [TIFF OMITTED] TP09MY18.022

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

[[Page 21203]]

[GRAPHIC] [TIFF OMITTED] TP09MY18.023

    (4) Before or upon accumulating 12,000 landings after the 
reinforcement modification required in paragraph (i)(2) or (3) of 
this AD, replace the reinforced front attachment on the fuselage 
side following the Description of Accomplishment Instructions in 
SOCATA Daher Service Bulletin SB 10-081, Revision 3, December 2017.

(j) Replacement of the Reinforced Front Attachment

    Replacement of the reinforced front attachment on the wing side 
and/or replacement of the reinforced front attachment on the 
fuselage side, does not terminate the inspections required in 
paragraphs (h)(1) and (i)(1) of this AD. After replacement, the 
initial and repetitive inspection cycle starts over.

(k) Credit for Previous Actions

    This AD allows credit for the initial inspection required in 
paragraphs (g)(1) and (i)(1) of this AD and any replacement that may 
have been required based on the initial inspection, if done before 
the effective date of this AD, following Socata Service Bulletin No. 
SB 10-081-57, Revison 1, dated August 1996 or Revision 2, dated 
January 2017. Any inspections or replacements done after the 
effective date must be done following SOCATA Daher Service Bulletin 
SB 10-081, Revision 3, December 2017 as specified in the Actions and 
Compliance of this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Small Airplane Standards Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, 
FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas 
City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-
4090; email: [email protected]. Before using any approved AMOC 
on any airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (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, Small Airplane 
Standards Branch, FAA; or the European Aviation Safety Agency 
(EASA).

(m) Related Information

    Refer to MCAI EASA No. 2018-0030, dated January 31, 2018; and 
Daher Service Bulletin SB 10-081, Revision 3, dated December 2017, 
for related information. You may examine the MCAI on the internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0326. For service information related to this AD, contact 
SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone: 
+33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email: 
[email protected]; internet: https://www.mysocata.com/login/accueil.php. You may review copies of the referenced 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.

    Issued in Kansas City, Missouri, on April 30, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification 
Service.
[FR Doc. 2018-09602 Filed 5-8-18; 8:45 am]
BILLING CODE 4910-13-P