Airworthiness Directive · Amendment 39-21378 · Propellers/propulsors
M7 Aerospace LLC Airplanes
This AD applies to M7 Aerospace LLC Model SA26-AT and SA26-T airplanes, all serial numbers, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for M7 Aerospace LLC Models SA26-AT and SA26-T airplanes. This AD was prompted by reports of the airplane power lever linkage detaching from the TPE331 engine propeller pitch control (PPC) shaft. This AD requires repetitively inspecting the PPC for proper torque and making any necessary corrections until the replacement of the PPC assembly and the installation of a secondary retention feature (safety wire) are done. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Within 100 hours time-in-service (TIS) after the effective date of this AD and thereafter at intervals not to exceed 100 hours TIS, inspect the security of the PPC lever by pulling the PPC lever upward by hand to ensure it does not detach from the PPC input shaft. If the PPC lever detaches during any inspection, before further flight, comply with paragraphs (h) and (i) of this AD.
(2) The replacement/re-identification required by paragraph (h) of this AD and the installation of the secondary retention feature (safety wire) required by paragraph (i) of this AD terminate the repetitive inspections of the PPC lever attachment required by paragraph (g)(1) of this AD.
Within 600 hours TIS after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, unless required before further flight by paragraph (g)(1) of this AD, do the actions in either paragraph (h)(1) or (2) of this AD in accordance with the Accomplishment Instructions in Honeywell International Inc. Service Bulletin TPE331-72-2190, dated December 21, 2011, except you are not required to report information to the manufacturer.
(1) Replace the PPC assembly with the applicable new design PPC assembly.
(2) Inspect the splined end of the shouldered shaft for the presence and condition of a threaded hole and, before further flight, repair or replace the cam assembly or rework the PPC assembly, as necessary, and re-identify the shouldered shaft.
Before further flight after completing the actions required by paragraph (h) of this AD, install the secondary retention feature (safety wire) on the airplane PPC lever and the PPC assembly.
Note 1 to paragraph (i): Paragraph j. of M7 Aerospace SA26 Series Maintenance Manual Temporary Revision 4-02, dated July 22, 2020, contains information related to installation of the secondary retention feature (safety wire).
