AD 2020-11-06 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

Makes named: pilatus. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Pilatus Aircraft Ltd. Models PC-6, 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, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes, all serial numbers, certificated in any category, with a left-hand or right-hand flap actuator assembly part number (P/N) 6132.0039.51 or P/N 6132.0039.52 or pushrod assembly P/N 6132.0040.00 installed, except those assemblies supplied by Pilatus Aircraft Ltd. with a European Aviation Safety Agency (EASA) form 1 tag dated July 2, 2018 or later. Note 1 to paragraph (c) of this AD: These airplanes may also be identified as Fairchild Republic Company airplanes, Fairchild Industries airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes.

Unless already done, do the following actions in paragraphs (f)(1) and (2) of this AD: (1) Within the next 100 hours time-in-service after June 30, 2020 (the effective date of this AD) or within the next 12 months after June 30, 2020 (the effective date of this AD), whichever occurs first, prepare the airplane and inspect each flap actuator taper pin for correct installation by following the Accomplishment Instructions-Part 1-On Aircraft, paragraphs 3.A through 3.B(2), of Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 27-005, dated July 2, 2018 (Pilatus SB No. 27-005). (i) If a taper pin has any damage, before further flight, replace and swage the taper pin and reinstall the pushrod assembly by following the Accomplishment Instructions-Part 1-On Aircraft, paragraphs 3.C and 3.D of Pilatus SB No. 27-005. (ii) If a taper pin is incorrectly swaged or is not swaged, before further flight, swage the taper pin and reinstall the pushrod assembly by following the Accomplishment Instructions-Part 1-On Aircraft, paragraphs 3.C and 3.D of Pilatus SB No. 27-005. (2) After June 30, 2020 (the effective date of this AD), do not install a flap actuator assembly, P/N 6132.0039.51 or P/N 6132.0039.52, or pushrod assembly P/N 6132.0040.00 on any airplane unless the part was supplied by Pilatus Aircraft Ltd. with an EASA form 1 tag dated July 2, 2018 or later, or the part has been inspected in accordance with paragraphs (f)(1)(i) and (ii) of this AD.

The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA, or EASA.

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated 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 flap actuator taper pins that were not swaged during the manufacturing process. The FAA is issuing this AD to prevent loss of one or both taper pins that could lead to asymmetric flap deployment or flap surface flutter and result in loss of control of the airplane.

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