Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

[Federal Register Volume 85, Number 151 (Wednesday, August 5, 2020)]
[Rules and Regulations]
[Pages 47295-47297]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-16989]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0536; Product Identifier 2018-CE-054-AD; Amendment 
39-21186; AD 2020-16-02]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

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

ACTION: Final rule.

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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 rudder shaft assemblies with incorrect rivet 
configurations. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective September 9, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 9, 
2020.

ADDRESSES: 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">techsupport@pilatus-aircraft.com; internet: https://
www.pilatus-aircraft.com. You may view this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 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

[[Page 47296]]

searching for and locating Docket No. FAA-2019-0536.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0536; 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 NPRM, any comments received, and other 
information. The street address for Docket Operations 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: 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 July 5, 2019 (84 FR 32099). The NPRM proposed to 
correct an unsafe condition for the specified products and was based on 
AD No. 2018-0222, dated October 19, 2018, issued by the European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Community (referred to after this as 
``the MCAI''). The MCAI states:

    During a recent check flight with a PC-6, the pilot experienced 
loss of rudder control. The consequent precautionary landing 
resulted in a runway excursion and damage to the aeroplane, but 
without serious injuries to the occupants. The post-event inspection 
of the affected rudder shaft assembly found an incorrect rivet 
configuration. Subsequent investigation results identified that the 
tapered pins had been replaced with an insufficient quantity of 
rivets of unknown origin, which effectively constituted a 
modification that does not conform to any of the three different 
Pilatus-approved configurations. Prompted by this event, five more 
aeroplanes were inspected and various non-standard rivet 
configurations were found in the same area. It cannot be excluded 
that more PC-6 aeroplanes have had a similar modification applied.
    This condition, if not detected and corrected, could lead to 
failure or loss of rivets, possibly resulting in reduced control of 
the aeroplane.
    To address this potential unsafe condition, Pilatus Aircraft Ltd 
issued the [service bulletin] SB to provide inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the affected part to determine the rivet 
configuration and, depending on findings, accomplishment of 
applicable corrective action(s). This [EASA] AD also requires 
inspection of affected parts held as spare, and depending on 
findings, corrective action(s), prior to installation.

    You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0536.

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD. The FAA received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting the AD as proposed.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Pilatus PC-6 Service Bulletin No. 27-006, Rev. No. 
1, dated September 4, 2018. The service information contains procedures 
for inspecting the rivet configuration on the rudder shaft assembly for 
size, quantity, location, and type and contacting Pilatus to obtain 
repair instructions if any discrepancies are found. 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 7 work-hours 
per product to comply with the inspection requirement of this AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, the FAA estimates the cost of this AD on 
U.S. operators to be $17,850, or $595 per product.
    Since the repair instructions could vary significantly from 
airplane to airplane if discrepancies are found during the inspections, 
the FAA has no way of determining the number of products that may need 
follow-on actions or what the cost per product would be.

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.

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) Will not affect intrastate aviation in Alaska, and
    (3) 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):


[[Page 47297]]


2020-16-02 Pilatus Aircraft Ltd.: Amendment 39-21186; Docket No. 
FAA-2019-0536; Product Identifier 2018-CE-054-AD.

(a) Effective Date

    This AD becomes effective September 9, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pilatus Aircraft Ltd. (Pilatus) 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.

    Note 1 to paragraph (c) of this AD:  These airplanes may also be 
identified as Fairchild Republic Company 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 rudder shaft 
assemblies with incorrect rivet configuration. The FAA is issuing 
this AD to prevent rudder shaft assembly failure, which could result 
in reduced control of the airplane.

(f) Actions and Compliance

    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 September 9, 
2020 (the effective date of this AD) or within the next 12 months 
after September 9, 2020 (the effective date of this AD), whichever 
occurs first, inspect the rudder shaft assembly for proper rivet 
configuration and repair any discrepancies before further flight in 
accordance with the Accomplishment Instructions--Part 1, paragraph 
3.B. and table 1, of Pilatus PC-6 Service Bulletin No: 27-006, Rev. 
No. 1, dated September 4, 2018.
    (2) After September 9, 2020 (the effective date of this AD), do 
not install a rudder shaft assembly on any airplane unless it has 
been inspected in accordance with paragraph (f)(1) of this AD and 
found to be free of discrepancies or all discrepancies have been 
repaired or replaced.

(g) 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.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency AD No. 2018-0222, 
dated October 19, 2018, for related information. The MCAI can be 
found in the AD docket on the internet at: https://www.regulations.gov by searching for and locating Docket No. FAA-
2019-0536.

(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 No: 27-006, Rev. No. 1, dated 
September 4, 2018.
    (ii) [Reserved]
    (3) 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">techsupport@pilatus-aircraft.com; 
internet: https://www.pilatus-aircraft.com.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 
Airworthiness Products Section, 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 and locating Docket No. 
FAA-2019-0536.
    (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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 28, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-16989 Filed 8-4-20; 8:45 am]
BILLING CODE 4910-13-P

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