2018-21-06: Wings

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 98-16-03, Amendment 39-10677 (63 FR 40359, July 29, 1998) and adding the following new AD: 2018-21-06 SOCATA: Amendment 39-19464; Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD. (a) Effective Date This AD becomes effective December 10, 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. [[Page 55260]] (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, the ``XX'' in the kit numbers 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 paragraphs B(1) through B(4) under the Description of Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-081, Revision 3, December 2017 (SB 10-081, Revision 3). [GRAPHIC] [TIFF OMITTED] TR05NO18.003 (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. Follow paragraph B(5) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. (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. Follow paragraph B(5) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. [GRAPHIC] [TIFF OMITTED] TR05NO18.004 (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 paragraphs B(1) through B(4) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. [[Page 55261]] [GRAPHIC] [TIFF OMITTED] TR05NO18.005 (2) Replacingkit 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 paragraph B(5) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. (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. Follow paragraph B(5) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. (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 paragraphs B(1) through B(4) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. [GRAPHIC] [TIFF OMITTED] TR05NO18.006 (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. Follow paragraph B(5) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. (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. Follow paragraph B(5)(b) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. [[Page 55262]] [GRAPHIC] [TIFF OMITTED] TR05NO18.007 (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. Follow paragraph B(5)(c) under the Description of Accomplishment Instructions in SB 10-081, Revision 3. (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 inspections required in paragraphs (g)(1), (h)(1), and (i)(1) of this AD if done before the effective date of this AD by following Socata Service Bulletin No. SB 10-081-57, Revision 1, dated August 1996 or Revision 2, dated January 2017. This AD also allows credit for any replacement that may have been required based on the initial inspection required in paragraphs (g)(1), (h)(1), and (i)(1) of this AD if done before the effective date of this AD by following Socata Service Bulletin No. SB 10-081-57, Revision 1, dated August 1996 or Revision 2, dated January 2017. After the effective date of this AD, you mustdo any inspections or replacements by following SB 10-081, Revision 3. (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: Quentin Coon, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4168; fax: (816) 329-4090; email: quentin.coon@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 instead 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 Socata Service Bulletin No. SB 10-081-57, Revision 1, dated August 1996, or Revision 2, dated January 2017, for related information. The MCAI can be found in the AD docket on the internet at: https://www.regulations.gov/document?D=FAA-2018-0326-0003. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) SOCATA Daher Service Bulletin SB 10-081, Revision 3, December 2017. (ii) [Reserved] (3) For service information identified in 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. (4) You may view this service information at FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816-329-4148. In addition, you can access this service information on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0326. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. [[Page 55263]]