Airworthiness Directive · Amendment 39-19464 · Wings
SOCATA Airplanes
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.
We are superseding Airworthiness Directive (AD) 98-16-03 for SOCATA Model TB 9 and Model TB 10 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 require actions to address the unsafe condition on these products.
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.
(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).
(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.
(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.
(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 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.
(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.
(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.
(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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
