Airworthiness directives › 2016-22-12
AD 2016-22-12 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Makes named: pilatus. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(1) This AD applies to PILATUS Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes, all manufacturer serial numbers, including MSN 2001 through 2092 (see Note 1 of paragraph c), certificated in any category. Note 1 of paragraph (c): For MSN 2001-2092, these airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes. (2) For the purpose of this AD, an “affected part” is any stabilizer-trim attachment component and the related parts and structure, as identified in Pilatus Aircraft Ltd. (Pilatus) PC-6 Service Bulletin (SB) No. 53-003, Revision 1, dated October 13, 2016.
Compliance
Unless already done, do the following actions. (1) For MSN 337 through 1005 and 2001 through 2092: Before further flight after November 4, 2016 (the effective date of this AD), do a visual inspection of the affected stabilizer-trim attachment and structural components following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (2) For MSN 337 through 1005 and 2001 through 2092: Within the next 100 hours time-in-service after November 4, 2016 (the effective date of this AD), do a visual inspection and dye-penetrant or eddy current inspection of the affected stabilizer-trim attachment and structural components following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (3) For MSN 337 through 1005 and 2001 through 2092: If any crack is found during any inspection required by paragraphs (f)(1) and (2) of this AD, before further flight, replace the affected part with a serviceable part following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. For the purpose of this AD, a “serviceable part” is an affected part that is new, or has passed an inspection before installation following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (4) For MSN 337 through 1005 and 2001 through 2092: Within 10 days after the inspections required by paragraphs (f)(1) and (2) of this AD or within the next 10 days after the effective date of this AD, whichever occurs later, report the results to Pilatus at the address in paragraph (j)(3) of this AD using the Report Form in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (5) For all affected MSNs: As of November 4, 2016 (the effective date of this AD), an affected part listed in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016, may be installed provided it is a serviceable part. For the purpose of this AD, a “serviceable part” is an affected part that is new, or has passed an inspection before installation following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016.
Required actions
This AD allows credit for the visual inspection required in paragraph (f)(1) of this AD if done before November 4, 2016 (the effective date of this AD), following Pilatus PC-6 SB No. 53-003, dated October 4, 2016. The dye-penetrant or eddy current inspection must still be done following Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016.
Unsafe condition
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 wear and cracks on the stabilizer-trim attachment and structural components. This condition, if not corrected, could cause failure of the stabilizer control system fitting or connecting piece, which could result in disconnection of the horizontal stabilizer rear attachment with consequent loss of control.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1