Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 12405-12407 [2017-03719]

Download as PDF Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations (viii) Airbus Service Bulletin A300–53– 0374, Revision 04, dated July 5, 2013. (ix) Airbus Service Bulletin A300–53– 0375, Revision 01, dated June 24, 2013. (x) Airbus Service Bulletin A300–53–0393, dated September 27, 2013. (xi) Airbus Service Bulletin A300–57– 0203, Revision 04, dated February 18, 2015. (xii) Airbus Service Bulletin A300–57– 0258, dated September 30, 2014. (xiii) Airbus Service Bulletin A300–57– 0259, dated September 30, 2014. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office–EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: continued.airworthiness-wb.external@ airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on February 16, 2017. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03951 Filed 3–2–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9357; Directorate Identifier 2016–CE–030–AD; Amendment 39–18798; AD 2017–04–03] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting 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 AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct mstockstill on DSK3G9T082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 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 AD to require actions to address the unsafe condition on these products. DATES: This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 7, 2017. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9357; or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. For service information identified in this 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: supportPC12@pilatus-aircraft.com; Internet: http://www.pilatusaircraft.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA–2016– 9357. FOR FURTHER INFORMATION CONTACT: 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: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to 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. The NPRM was published in the Federal Register on November 4, 2016 (81 FR 76883). The NPRM proposed to correct an unsafe condition PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 12405 for the specified products and was based on mandatory continuing airworthiness information (MCAI) 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). The MCAI can be found in the AD docket on the Internet at: https://www. regulations.gov/document?D=FAA2016-9357-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and the FAA’s response to the comment. Request for Clarification on the Unsafe Condition Lukas Owens stated that in the event of loss of the ailerons, some degree of roll control is available by using the secondary effect of rudder. The requester stated that while not an efficient way to turn the aircraft, a pilot has at least some directional control and that short or rapid bursts of power may increase the effectiveness of the rudder to some degree, acting as a form of torque and slipstream effect. The requester asked why the AD change is needed or how it is justified. We infer that the commenter, in addition to asking why the AD action is necessary and how it is justified, believes the AD action is not needed and is not justified. However, the commenter does not present solutions that address the unsafe condition of the mass balance weight potentially separating from the airplane. For this reason, we have not changed this AD based on this comment. Conclusion We reviewed the relevant data, considered the comment received, and E:\FR\FM\03MRR1.SGM 03MRR1 12406 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 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 ADDRESSES section of this document. Costs of Compliance We estimate that this 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 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 this AD on U.S. operators to be $8,100, or $270 per product. mstockstill on DSK3G9T082PROD with RULES Authority for This Rulemaking 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. Regulatory Findings We determined that this AD will not have federalism implications under VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 Executive Order 13132. This AD will 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 AD: (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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9357; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2017–04–03 Pilatus Aircraft Limited: Amendment 39–18798; Docket No. FAA–2016–9357; Directorate Identifier 2016–CE–030–AD. (a) Effective Date This airworthiness directive (AD) becomes effective April 7, 2017. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 (b) Affected ADs None. (c) Applicability 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, certificated in any category. Note 1 of paragraph (c) of this AD: 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. (d) Subject Air Transport Association of America (ATA) Code 57: Wings. (e) Reason 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 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 AD to prevent disconnection of the aileron counterweight from the aileron, which could result in loss of control. (f) Actions and Compliance 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 April 7, 2017 (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. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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 Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; E:\FR\FM\03MRR1.SGM 03MRR1 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (h) Related Information Refer to MCAI EASA AD No.: 2016–0183, dated September 13, 2016, for related information. The MCAI can be found in the AD docket on the Internet at: https:// www.regulations.gov/document?D=FAA2016-9357-0002. (i) Material Incorporated by Reference mstockstill on DSK3G9T082PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Pilatus PC–6 Service Bulletin (SB) No. 57–006, dated May 13, 2016. (ii) Reserved. (3) For Pilatus Aircraft Ltd. service information identified in this 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: supportPC12@pilatus-aircraft.com; Internet: http://www.pilatus-aircraft.com. (4) You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. In addition, you can access this service information on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–9357. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri on February 8, 2016. Robert Busto, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03719 Filed 3–2–17; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6893; Directorate Identifier 2015–NM–181–AD; Amendment 39–18812; AD 2017–05–02] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318–112 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321– 211, –212, –213, –231, and –232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 7, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6893. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 12407 6893; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318– 112 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321–211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on May 26, 2016 (81 FR 33438). The NPRM was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. The NPRM proposed to require a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0218, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318–112 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321–211, –212, –213, –231, and –232 airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that wrong aluminum alloy were delivered E:\FR\FM\03MRR1.SGM 03MRR1

Agencies

[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)]
[Rules and Regulations]
[Pages 12405-12407]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03719]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9357; Directorate Identifier 2016-CE-030-AD; 
Amendment 39-18798; AD 2017-04-03]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting 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 AD results 
from mandatory continuing airworthiness information (MCAI) issued 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 AD to require actions to address the unsafe 
condition on these products.

DATES: This AD is effective April 7, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 7, 
2017.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9357; or in person at Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
    For service information identified in this 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: aircraft.com">supportPC12@pilatus-aircraft.com; Internet: http://www.pilatus-
aircraft.com. You may view this referenced service information at the 
FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the FAA, 
call (816) 329-4148. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA-2016-9357.

FOR FURTHER INFORMATION CONTACT: 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: 
doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to 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. The NPRM was published in the 
Federal Register on November 4, 2016 (81 FR 76883). The NPRM proposed 
to correct an unsafe condition for the specified products and was based 
on mandatory continuing airworthiness information (MCAI) 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).

The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/document?D=FAA-2016-9357-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the proposal 
and the FAA's response to the comment.

Request for Clarification on the Unsafe Condition

    Lukas Owens stated that in the event of loss of the ailerons, some 
degree of roll control is available by using the secondary effect of 
rudder. The requester stated that while not an efficient way to turn 
the aircraft, a pilot has at least some directional control and that 
short or rapid bursts of power may increase the effectiveness of the 
rudder to some degree, acting as a form of torque and slipstream 
effect. The requester asked why the AD change is needed or how it is 
justified.
    We infer that the commenter, in addition to asking why the AD 
action is necessary and how it is justified, believes the AD action is 
not needed and is not justified. However, the commenter does not 
present solutions that address the unsafe condition of the mass balance 
weight potentially separating from the airplane. For this reason, we 
have not changed this AD based on this comment.

Conclusion

    We reviewed the relevant data, considered the comment received, and

[[Page 12406]]

determined that air safety and the public interest require adopting the 
AD as proposed except for minor editorial changes. We have determined 
that these minor changes:

     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than 
was already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    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 ADDRESSES section 
of this document.

Costs of Compliance

    We estimate that this 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 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 this AD on U.S. 
operators to be $8,100, or $270 per product.

Authority for This Rulemaking

    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.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    (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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9357; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the NPRM, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone (800) 647-5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2017-04-03 Pilatus Aircraft Limited: Amendment 39-18798; Docket No. 
FAA-2016-9357; Directorate Identifier 2016-CE-030-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective April 7, 
2017.

 (b) Affected ADs

    None.

 (c) Applicability

    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, certificated in any category.

    Note 1 of paragraph (c) of this AD: 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.

 (d) Subject

    Air Transport Association of America (ATA) Code 57: Wings.

 (e) Reason

    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 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 AD to prevent disconnection of the aileron 
counterweight from the aileron, which could result in loss of 
control.

 (f) Actions and Compliance

    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 April 7, 2017 (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.

 (g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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 Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106;

[[Page 12407]]

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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

 (h) Related Information

    Refer to MCAI EASA AD No.: 2016-0183, dated September 13, 2016, 
for related information. The MCAI can be found in the AD docket on 
the Internet at: https://www.regulations.gov/document?D=FAA-2016-9357-0002.

 (i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Pilatus PC-6 Service Bulletin (SB) No. 57-006, dated May 13, 
2016.
    (ii) Reserved.
    (3) For Pilatus Aircraft Ltd. service information identified in 
this 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: aircraft.com">supportPC12@pilatus-aircraft.com; Internet: http://www.pilatus-aircraft.com.
    (4) You may review this referenced service information at the 
FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
FAA, call (816) 329-4148. In addition, you can access this service 
information on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-9357.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri on February 8, 2016.
Robert Busto,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03719 Filed 3-2-17; 8:45 am]
 BILLING CODE 4910-13-P