Federal Aviation Administration (FAA), Department of Transportation (DOT).
Notice of proposed rulemaking (NPRM).
We propose to adopt a new airworthiness directive (AD) for Pilatus Aircraft Ltd. 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. This proposed AD results from 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 certain combinations of the aileron counterweight and the attaching parts possibly resulting in reduced thread engagement and leading to disconnection of the aileron counterweight from the aileron. We are issuing this proposed AD to require actions to address the unsafe condition on these products.
We must receive comments on this proposed AD by December 19, 2016.
You may send comments by any of the following methods:
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For service information identified in this proposed AD, contact Pilatus Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 3333; fax: +41 (0)41 619 7311; email:
You may examine the AD docket on the Internet at
Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329–4090; email:
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the
We will post all comments we receive, without change, to
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2016–0183, dated September 13, 2016 (referred to after this as “the MCAI”), to correct an unsafe condition for Pilatus Aircraft Ltd. Model 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 and was based on mandatory continuing airworthiness information originated by an aviation authority of another country. The MCAI states:
The proper installation of the aileron counterweight requires a combination, peculiar to each aileron, of anchor nut types, bolt types, number of washers, and the definition of the bolt torque. Some combinations of counterweight and attaching parts, which could result in reduced thread engagement, have been reported on a PC–6 aeroplane.
This condition, if not detected and corrected, may lead to a disconnection of the aileron counterweight from the aileron, possibly resulting in reduced control of the aeroplane.
To address this potential unsafe condition, Pilatus issued Service Bulletin (SB) No. 57–006 (hereafter referred to as `the SB' in this AD) to provide inspection instructions.
For the reason described above, this AD requires identification and inspection of the affected aileron mass-balance counterweight attachment parts and, depending on findings, accomplishment of applicable corrective action(s).
You may examine the MCAI on the Internet at
Pilatus Aircraft Ltd. has issued Pilatus PC–6 Service Bulletin No. 57–006, dated May 13, 2016. The service information describes procedures for removal, installation, and inspection of the ailerons, aileron balance tabs, and the aileron counterweights and their attaching parts. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the
This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.
We estimate that this proposed AD will affect 30 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $100 per product.
Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $8,100, or $270 per product.
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs,” describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in “Subtitle VII, Part A, Subpart III, Section 44701: General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed regulation:
(1) Is not a “significant regulatory action” under Executive Order 12866,
(2) Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
We must receive comments by December 19, 2016.
None.
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 (MSN), including MSN 2001 through 2092 (see Note 1 of paragraph c), certificated in any category.
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.
Air Transport Association of America (ATA) Code 57: Wings.
This AD was prompted by certain combinations of the aileron counterweight and the attaching parts possibly resulting in reduced thread engagement and leading to disconnection of the aileron counterweight from the aileron. We are issuing this proposed AD to prevent disconnection of the aileron counterweight from the aileron, which could result in loss of control.
Unless already done, do the following actions as specified in paragraphs (f)(1) and (2) of this AD:
(1) Within the next 12 months after the effective date of this AD or the next time the ailerons or aileron counterweights are removed or installed, whichever occurs first, and thereafter anytime the ailerons or aileron counterweights are removed or installed, remove each aileron counterweight to inspect the type and number of washers required for the installation of a counterweight on each aileron following the accomplishment instructions of paragraphs 3.B.(2) and 3.B.(3) of Pilatus PC–6 Service Bulletin (SB) No. 57–006, dated May 13, 2016.
(2) Before further flight after the inspection required by paragraph (f)(1) of this AD, reinstall each aileron counterweight on the airplane following the accomplishment instructions of paragraph 3.B.(3) of Pilatus PC–6 SB No. 57–006, dated May 13, 2016.
The following provisions also apply to this AD:
(1)
(2)
Refer to MCAI EASA AD No.: 2016–0183, dated September 13, 2016, for related information. You may examine the MCAI on the Internet at