Airworthiness directives › 2016-25-12
AD 2016-25-12 Airworthiness Directives; M7 Aerospace LLC
Applicability*9
This AD applies to M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes, all serial numbers, certificated in any category.
Compliance
Comply with paragraphs (g)(1) and (2) of this AD using the following service bulletins and within the compliance times specified, unless already done: (1) For Models SA226-AT, SA226-T, SA226-T(B), and SA226-TC: M7 Aerospace LLC Service Bulletin (SB) 226-27-081 R1, revised June 27, 2016; or (2) For Models SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), and SA227-TT: M7 Aerospace LLC SB 227-27-061 R1, revised June 27, 2016; or (3) For Models SA227-CC and SA227-DC (C-26B): M7 Aerospace LLC SB CC7-27-033 R1, revised June 27, 2016.
Required actions
(1) Within the next 600 hours time-in-service (TIS) after January 12, 2017 (the effective date of this AD) or within the next 12 months after January 12, 2017 (the effective date of this AD), whichever occurs first, and repetitively thereafter at intervals not to exceed every 5,000 hours TIS or 5 years, whichever occurs first, perform the inspection of the pitch trim actuator upper attach fittings following section 2.A. and return to service following section 2.C. of the Accomplishment Instructions of the service bulletins identified in paragraph (f)(1), (2), or (3) of this AD, as applicable. (2) If any corrosion or cracks are found as a result of any inspection in paragraph (g)(1) of this AD, before further flight, replace the fitting following section 2.B. and return to service following section 2.C. of the Accomplishment Instructions of the service bulletins identified in paragraph (f)(1), (2), or (3) of this AD, as applicable.
Unsafe condition
This AD was prompted by corrosion and stress corrosion cracking of the pitch trim actuator upper attach fittings of the horizontal stabilizer front spar. We are issuing this AD to prevent jamming and/or loss of control of the horizontal stabilizer, which could result in partial or complete loss of airplane pitch control.
Affected ADs
None.
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