Airworthiness Directive · Amendment 39-15673 · Electric power
EADS SOCATA Model TBM 700 Airplanes
Superseded. A later AD replaced this one: AD 2011-02-02. Comply with the one in force.
This AD applies to Models TBM 700 airplanes, all serial numbers beginning with 434, certificated in any category.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, for airplanes S/N 434 through 459 only, before further flight after October 8, 2008 (the effective date of this AD), do the following actions following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated July 2008:
(1) Remove the pulley drive assembly, the torque limiter, the compressor drive belt, and the alternator/compressor support.
(2) Inspect for cracks on the pulley drive surfaces and the alternator/compressor support welds.
(i) If any crack is detected, replace the pulley drive assembly or conditionally repair the cracked unit following the accomplishment instructions in section D.2 of EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated July 2008.
(ii) Replacement of the assembly incorporates replacement of the pulley drive sheer shaft required by paragraph (f)(3) of this AD for airplanes with 30 hours TIS or more with the torque limiter installed on the pulley drive shear shaft.
(3) Replace any pulley drive shear shaft that has accumulated 30 hours TIS or more with the torque limiter installed. This action is not required if you replaced the whole assembly per paragraph (f)(2)(i) of this AD.
(4) Re-install the pulley drive assembly and the alternator/compressor support, without re-installing the compressor drive belt or the torque limiter.
(5) Install on the instrument panel and in the pilot's primary field of vision, the following placard:
and insert EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated July 2008 in the limitations section of the pilot's operating handbook.
(g) For all serial number airplanes;
(1) Within 100 hours TIS after October 8, 2008 (the effective date of this AD), and thereafter at intervals not to exceed 100 hours TIS, inspect for cracks on the pulley drive surfaces and the alternator/compressor support welds, following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated July 2008. For accomplishment of the repetitive inspections required by paragraph (g)(1) of this AD, paragraph C.2 of the accomplishment instructions of EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated July 2008, does not apply since the torque limiter has already been removed.
(2) If cracks are found during any of these inspections, before further flight, replace the assembly or conditionally repair the unit following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated July 2008. The 100-hour TIS repetitive inspections are still required after replacement or repair.
(h) As an alternative to the requirements of paragraphs (f) and (g) of this AD, do the following actions before further flight after October 8, 2008 (the effective date of this AD), following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 3, dated July 2008:
(1) Install a zero-timed pulley drive assembly P/N T700G215510000000 following the accomplishment instructions in section D.1, I and J of EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 3, dated July 2008.
(2) Within 100 hours TIS after the installation required in paragraph (h)(1) of this AD and repetitively thereafter at intervals not to exceed 100 TIS, inspect the alternator/compressor support welds for cracks following the accomplishment instructions in sections B,G, H, I, and J of EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 3, dated July 2008.
(3) If any crack is detected in the inspection required in paragraph (h)(2) of this AD, before further flight, replace or repair the cracked unit following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, amendment 3, dated July 2008.
(4) Upon the accumulation of 400 hours TIS, replace each pulley drive assembly, P/N T700G215510000000, with a zero-timed one.
Note 1: Compliance with the requirements of paragraph (h) of this AD restores the capability to make use of the air conditioning system.
Note 2: This AD differs from the MCAI and/or service information as follows: No differences.
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.
