Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 25982-25984 [2019-11747]

Download as PDF 25982 Federal Register / Vol. 84, No. 108 / Wednesday, June 5, 2019 / Rules and Regulations (i.e., block floor proximity lights to the extent that the lights no longer meet their intended function). Issued in Des Moines, Washington, on May 30, 2019. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2019–11666 Filed 6–4–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1058; Product Identifier 2018–CE–051–AD; Amendment 39–19646; AD 2019–10–07] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Discussion Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for 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. 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 sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. The FAA is issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective July 10, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 10, 2019. ADDRESSES: You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 1058; or in person at Docket Operations, 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., jbell on DSK3GLQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:38 Jun 04, 2019 Jkt 247001 Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 73; email: techsupport@pilatus-aircraft.com; internet: https://www.pilatusaircraft.com. You may view this referenced service information at the FAA, Policy and Innovation Division, 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 https:// www.regulations.gov by searching for Docket No. FAA–2018–1058. FOR FURTHER INFORMATION CONTACT: 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. SUPPLEMENTARY INFORMATION: The FAA 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–6/350, 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. The NPRM was published in the Federal Register on December 26, 2018 (83 FR 66175). The NPRM proposed to correct an unsafe condition for the specified products and was based on MCAI AD No. 2018–0217, dated October 10, 2018, issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI states: During a routine inspection, the rivets of the hinge bracket assemblies on a Pilatus PC– 6 were found to be sheared or missing. Investigation results identified that this was most likely due to application of too much force to the ends of the horizontal stabilizer during ground handling. This condition, if not detected and corrected, could lead to failure of the primary horizontal stabilizer load path and consequent separation of the horizontal stabilizer, possibly resulting in loss of control of the aeroplane. To address this potential unsafe condition, Pilatus Aircraft Ltd issued the SB [service bulletin] to provide applicable inspection instructions. For the reasons described above, this [EASA] AD requires a one-time inspection of the affected parts and the horizontal stabilizer front spar attachment area and, depending on findings, accomplishment of applicable corrective action(s). This [EASA] AD also requires, before installation, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 inspection of, and, depending on findings, corrective action(s) on, affected parts held as spare. The amount of force to the ends of the horizontal stabilizer cannot be quantified; however, fleet experience shows that repetitive pushing or pulling on the horizontal stabilizer to move the airplane on the ground can overload the rivets. Although a root cause could not be determined, due to the severity of separation of a horizontal stabilizer, EASA determined that the corrective actions should be required for other airplanes of the same type design. Pilatus Aircraft Ltd. had previously considered the small size of the original ‘‘DO NOT PUSH’’ markings and the significant chance of the markings being over-sprayed during a respray. As a result, Pilatus Aircraft Ltd. issued a service bulletin to specify replacing the smaller markings with new, larger placards. The FAA requires installing these placards in this AD. The MCAI can be found in the AD docket on the internet at https:// www.regulations.gov/document? D=FAA-2018-1058-0002. Comments The FAA 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 the comment. Request To Add Omitted Section to Required Procedures Pilatus Aircraft Ltd. requested that the FAA amend the required actions to include section H of the Accomplishment Instructions in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 55–004, dated July 2, 2018. The commenter notes that section H was omitted and should be added to the final rule. The FAA agrees with the commenter and has changed paragraph (f)(1)(i) to include section H. Conclusion The FAA reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. The FAA determined that this change is consistent with the intent that was proposed in the NPRM for correcting the unsafe condition and does not add any additional burden upon the public than was already proposed in the NPRM. The FAA also determined that this change will not increase the economic burden on any operator or increase the scope of the AD. E:\FR\FM\05JNR1.SGM 05JNR1 Federal Register / Vol. 84, No. 108 / Wednesday, June 5, 2019 / Rules and Regulations Related Service Information Under 1 CFR Part 51 Pilatus Aircraft Ltd. has issued PC–6 Service Bulletin No. 55–004, dated July 2, 2018. The service information contains procedures for inspecting the left-hand and right-hand horizontal stabilizer hinge bracket assemblies and, if any discrepancies are found, repairing or replacing any damaged rivets and screws. Pilatus Aircraft Ltd. has also issued PC–6 Service Bulletin No. 55– 002, Revision. No. 1, dated February 18, 2016. This service information contains procedures for inspecting and repairing the horizontal stabilizer attachment hardware and installing four ‘‘DO NOT PUSH’’ placards. 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. Costs of Compliance The FAA estimates that this AD will affect 30 products of U.S. registry. The FAA also estimates that it will take about 9 work-hours per product to comply with the inspection and placard requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $200 per product. Based on these figures, the FAA estimates the cost of the inspection and placard requirements on U.S. operators to be $28,950, or $965 per product. In addition, the FAA estimates the following to do any necessary follow-on actions: Each rivet replacement will take 2 work-hours, fastener replacement will take 3 work-hours, one hinge bracket assembly replacement will take 9 workhours, and two hinge bracket assembly replacements will take 15 work-hours. The total estimated cost of parts will be $10,000. The FAA has no way of determining the number of products that may need replacement. jbell on DSK3GLQ082PROD with RULES 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. The FAA is 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 16:38 Jun 04, 2019 Jkt 247001 Regulatory Findings The FAA 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. List of Subjects in 14 CFR Part 39 Authority for This Rulemaking VerDate Sep<11>2014 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division. 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. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 § 39.13 25983 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–10–07 Pilatus Aircraft Ltd.: Amendment 39–19646; Docket No. FAA–2018–1058; Product Identifier 2018–CE–051–AD. (a) Effective Date This AD becomes effective July 10, 2019. (b) Affected ADs None. (c) Applicability 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, PC–6–H2 airplanes, all serial numbers, certificated in any category. Note 1 to paragraph (c): These airplanes may also be identified as Fairchild Republic Company airplanes, Fairchild Industries airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes. (d) Subject Air Transport Association of America (ATA) Code 55: Stabilizers. (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 sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. The FAA is issuing this AD to prevent failure of the primary horizontal stabilizer load path, which could lead to separation of the horizontal stabilizer and result in loss of control of the airplane. (f) Actions and Compliance Unless already done, do the following actions in paragraphs (f)(1) and (2). (1) Within the next 100 hours time-inservice after July 10, 2019 (the effective date of this AD) or within the next 12 months after July 10, 2019 (the effective date of this AD), whichever occurs first: (i) Inspect the left-hand and the right-hand horizontal stabilizer hinge bracket assemblies for cracks, loose screws and rivets, sheared rivets, missing rivets, and looseness of the electrical bonding strap, and inspect the top and bottom screws at each hinge bracket. Repair or replace any parts with discrepancies before further flight. You must do the actions required by this paragraph by following sections C through H of the Accomplishment Instructions–Part 1–On Aircraft in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 55–004, dated July 2, 2018. (ii) Install four ‘‘DO NOT PUSH’’ placards, part number 110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by following section G of the Accomplishment Instructions—Aircraft in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 55–002, Revision. No. 1, dated February 18, 2016. E:\FR\FM\05JNR1.SGM 05JNR1 25984 Federal Register / Vol. 84, No. 108 / Wednesday, June 5, 2019 / Rules and Regulations (2) After July 10, 2019 (the effective date of this AD), do not install a horizontal stabilizer on any airplane unless it has been inspected as specified in paragraph (f)(1)(i) of this AD and found to be free of discrepancies or all discrepancies have been repaired or replaced. (g) Other FAA AD Provisions 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 the European Aviation Safety Agency (EASA). jbell on DSK3GLQ082PROD with RULES (h) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2018–0217, dated October 10, 2018, for related information. (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 Aircraft Ltd. PC–6 Service Bulletin No. 55–002, Revision. No. 1, dated February 18, 2016. (ii) Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 55–004, dated July 2, 2018. (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 67 74; fax: +41 (0)41 619 67 73; email: techsupport@pilatus-aircraft.com; internet: https://www.pilatus-aircraft.com. (4) You may view this service information at the FAA, Policy and Innovation Division, 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2018–1058. (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: https:// VerDate Sep<11>2014 16:38 Jun 04, 2019 Jkt 247001 www.archives.gov/federal-register/cfr/ibrlocations.html. searching for and locating Docket No. FAA–2018–0916. Issued in Kansas City, Missouri, on May 23, 2019. Melvin J. Johnson, Aircraft Certification Service, Deputy Director, Policy and Innovation Division, AIR–601. Examining the AD Docket [FR Doc. 2019–11747 Filed 6–4–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0916; Product Identifier 2018–NE–33–AD; Amendment 39– 19643; AD 2019–10–04] RIN 2120–AA64 Airworthiness Directives; BRP-Rotax GmbH & Co KG Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain BRP-Rotax GmbH & Co KG (Rotax) 912 and 914 model engines. This AD was prompted by power loss and engine revolutions per minute (RPM) drop on certain Rotax 912 and 914 model engines due to a quality control deficiency in the manufacturing process of certain valve push-rod assemblies resulting in partial wear on the rocker arm ball socket and possible malfunction of the valve. This AD requires one-time inspection and, depending on the findings, replacement of the affected parts with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 10, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 10, 2019. ADDRESSES: For service information identified in this final rule, contact BRPRotax GmbH & Co KG, Rotaxstrasse 1, A–4623 Gunskirchen, Austria; phone: +43 7246 601 0; fax: +43 7246 601 9130; email: airworthiness@brp.com; internet: www.flyrotax.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238– 7759. It is also available on the internet at https://www.regulations.gov by SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0916; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647– 5527) is 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: Wego Wang, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7134; fax: 781–238–7199; email: wego.wang@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 certain Rotax 912 and 914 model engines. The NPRM published in the Federal Register on November 6, 2018 (83 FR 55502). The NPRM was prompted by power loss and engine RPM drop on certain Rotax 912 and 914 model engines due to a quality control deficiency in the manufacturing process of certain valve push-rod assemblies resulting in partial wear on the rocker arm ball socket and possible malfunction of the valve. The NPRM proposed to require a one-time inspection and, depending on the findings, replacement of the affected parts with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products. The European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2017–0208, dated October 13, 2017 (referred to after this as ‘‘the MCAI’’), to address the unsafe condition on these products. The MCAI states: Power loss and engine RPM drop have been reported on Rotax 912/914 engines in service. It has been determined that, due to a quality control deficiency in the manufacturing process of certain valve pushrod assemblies, manufactured between 08 June 2016 and 02 October 2017 inclusive, partial wear on the rocker arm ball socket E:\FR\FM\05JNR1.SGM 05JNR1

Agencies

[Federal Register Volume 84, Number 108 (Wednesday, June 5, 2019)]
[Rules and Regulations]
[Pages 25982-25984]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11747]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1058; Product Identifier 2018-CE-051-AD; Amendment 
39-19646; AD 2019-10-07]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
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. 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 sheared or missing rivets on the horizontal 
stabilizer hinge bracket assemblies. The FAA is issuing this AD to 
require actions to address the unsafe condition on these products.

DATES: This AD is effective July 10, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 10, 2019.

ADDRESSES: You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1058; or in person at Docket Operations, 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 67 74; fax: +41 (0)41 619 67 
73; email: aircraft.com">[email protected]aircraft.com; internet: https://
www.pilatus-aircraft.com. You may view this referenced service 
information at the FAA, Policy and Innovation Division, 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 https://www.regulations.gov by searching for Docket No. 
FAA-2018-1058.

FOR FURTHER INFORMATION CONTACT: 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: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA 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-6/350, 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. The NPRM was published in the 
Federal Register on December 26, 2018 (83 FR 66175). The NPRM proposed 
to correct an unsafe condition for the specified products and was based 
on MCAI AD No. 2018-0217, dated October 10, 2018, issued by the 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Community. The MCAI states:

    During a routine inspection, the rivets of the hinge bracket 
assemblies on a Pilatus PC-6 were found to be sheared or missing. 
Investigation results identified that this was most likely due to 
application of too much force to the ends of the horizontal 
stabilizer during ground handling.
    This condition, if not detected and corrected, could lead to 
failure of the primary horizontal stabilizer load path and 
consequent separation of the horizontal stabilizer, possibly 
resulting in loss of control of the aeroplane.
    To address this potential unsafe condition, Pilatus Aircraft Ltd 
issued the SB [service bulletin] to provide applicable inspection 
instructions.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the affected parts and the horizontal stabilizer 
front spar attachment area and, depending on findings, 
accomplishment of applicable corrective action(s). This [EASA] AD 
also requires, before installation, inspection of, and, depending on 
findings, corrective action(s) on, affected parts held as spare.

    The amount of force to the ends of the horizontal stabilizer cannot 
be quantified; however, fleet experience shows that repetitive pushing 
or pulling on the horizontal stabilizer to move the airplane on the 
ground can overload the rivets. Although a root cause could not be 
determined, due to the severity of separation of a horizontal 
stabilizer, EASA determined that the corrective actions should be 
required for other airplanes of the same type design.
    Pilatus Aircraft Ltd. had previously considered the small size of 
the original ``DO NOT PUSH'' markings and the significant chance of the 
markings being over-sprayed during a respray. As a result, Pilatus 
Aircraft Ltd. issued a service bulletin to specify replacing the 
smaller markings with new, larger placards. The FAA requires installing 
these placards in this AD.
    The MCAI can be found in the AD docket on the internet at https://www.regulations.gov/document?D=FAA-2018-1058-0002.

Comments

    The FAA 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 the comment.

Request To Add Omitted Section to Required Procedures

    Pilatus Aircraft Ltd. requested that the FAA amend the required 
actions to include section H of the Accomplishment Instructions in 
Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-004, dated July 2, 
2018. The commenter notes that section H was omitted and should be 
added to the final rule.
    The FAA agrees with the commenter and has changed paragraph 
(f)(1)(i) to include section H.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety and the public interest 
require adopting the AD with the change described previously. The FAA 
determined that this change is consistent with the intent that was 
proposed in the NPRM for correcting the unsafe condition and does not 
add any additional burden upon the public than was already proposed in 
the NPRM. The FAA also determined that this change will not increase 
the economic burden on any operator or increase the scope of the AD.

[[Page 25983]]

Related Service Information Under 1 CFR Part 51

    Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 55-004, 
dated July 2, 2018. The service information contains procedures for 
inspecting the left-hand and right-hand horizontal stabilizer hinge 
bracket assemblies and, if any discrepancies are found, repairing or 
replacing any damaged rivets and screws. Pilatus Aircraft Ltd. has also 
issued PC-6 Service Bulletin No. 55-002, Revision. No. 1, dated 
February 18, 2016. This service information contains procedures for 
inspecting and repairing the horizontal stabilizer attachment hardware 
and installing four ``DO NOT PUSH'' placards. 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.

Costs of Compliance

    The FAA estimates that this AD will affect 30 products of U.S. 
registry. The FAA also estimates that it will take about 9 work-hours 
per product to comply with the inspection and placard requirements of 
this AD. The average labor rate is $85 per work-hour. Required parts 
will cost about $200 per product.
    Based on these figures, the FAA estimates the cost of the 
inspection and placard requirements on U.S. operators to be $28,950, or 
$965 per product.
    In addition, the FAA estimates the following to do any necessary 
follow-on actions: Each rivet replacement will take 2 work-hours, 
fastener replacement will take 3 work-hours, one hinge bracket assembly 
replacement will take 9 work-hours, and two hinge bracket assembly 
replacements will take 15 work-hours. The total estimated cost of parts 
will be $10,000. The FAA has no way of determining the number of 
products that may need replacement.

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.
    The FAA is 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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

Regulatory Findings

    The FAA 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.

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 airworthiness 
directive (AD):

2019-10-07 Pilatus Aircraft Ltd.: Amendment 39-19646; Docket No. 
FAA-2018-1058; Product Identifier 2018-CE-051-AD.

(a) Effective Date

    This AD becomes effective July 10, 2019.

(b) Affected ADs

    None.

(c) Applicability

    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, 
PC-6-H2 airplanes, all serial numbers, certificated in any category.

    Note 1 to paragraph (c): These airplanes may also be identified 
as Fairchild Republic Company airplanes, Fairchild Industries 
airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller 
Corporation airplanes.


(d) Subject

    Air Transport Association of America (ATA) Code 55: Stabilizers.

(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 sheared or 
missing rivets on the horizontal stabilizer hinge bracket 
assemblies. The FAA is issuing this AD to prevent failure of the 
primary horizontal stabilizer load path, which could lead to 
separation of the horizontal stabilizer and result in loss of 
control of the airplane.

(f) Actions and Compliance

    Unless already done, do the following actions in paragraphs 
(f)(1) and (2).
    (1) Within the next 100 hours time-in-service after July 10, 
2019 (the effective date of this AD) or within the next 12 months 
after July 10, 2019 (the effective date of this AD), whichever 
occurs first:
    (i) Inspect the left-hand and the right-hand horizontal 
stabilizer hinge bracket assemblies for cracks, loose screws and 
rivets, sheared rivets, missing rivets, and looseness of the 
electrical bonding strap, and inspect the top and bottom screws at 
each hinge bracket. Repair or replace any parts with discrepancies 
before further flight. You must do the actions required by this 
paragraph by following sections C through H of the Accomplishment 
Instructions-Part 1-On Aircraft in Pilatus Aircraft Ltd. PC-6 
Service Bulletin No. 55-004, dated July 2, 2018.
    (ii) Install four ``DO NOT PUSH'' placards, part number 
110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by 
following section G of the Accomplishment Instructions--Aircraft in 
Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-002, Revision. 
No. 1, dated February 18, 2016.

[[Page 25984]]

    (2) After July 10, 2019 (the effective date of this AD), do not 
install a horizontal stabilizer on any airplane unless it has been 
inspected as specified in paragraph (f)(1)(i) of this AD and found 
to be free of discrepancies or all discrepancies have been repaired 
or replaced.

(g) Other FAA AD Provisions

    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: [email protected]. 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 the European Aviation 
Safety Agency (EASA).

 (h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2018-0217, dated October 10, 2018, for related information.

(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 Aircraft Ltd. PC-6 Service Bulletin No. 55-002, 
Revision. No. 1, dated February 18, 2016.
    (ii) Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-004, 
dated July 2, 2018.
    (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 67 74; fax: +41 (0)41 619 67 73; email: aircraft.com">[email protected]aircraft.com; internet: https://www.pilatus-aircraft.com.
    (4) You may view this service information at the FAA, Policy and 
Innovation Division, 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 https://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-1058.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on May 23, 2019.
Melvin J. Johnson,
Aircraft Certification Service, Deputy Director, Policy and Innovation 
Division, AIR-601.
[FR Doc. 2019-11747 Filed 6-4-19; 8:45 am]
 BILLING CODE 4910-13-P

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