[Federal Register Volume 86, Number 107 (Monday, June 7, 2021)]
[Rules and Regulations]
[Pages 30155-30158]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-11812]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0857; Project Identifier MCAI-2020-00707-A; 
Amendment 39-21570; AD 2021-11-08]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2014-25-04 
for all Pilatus Aircraft Ltd. (Pilatus) 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. AD 2014-25-04 required incorporating revised airworthiness 
limitations into the aircraft maintenance manual (AMM) for your FAA-
approved maintenance program. This AD requires incorporating new 
airworthiness limitations and an eddy current inspection of each 
fuselage wing fitting if an earlier version of the service information 
was accomplished. This AD was prompted by a determination that the new 
life limits, revised airworthiness limitations, and new inspection 
procedures are necessary. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective July 12, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 12, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH-
6371 Stans, Switzerland; phone: +41 848 24 7 365; email: 
Techsupport@pilatus-

[[Page 30156]]

aircraft.com; website: https://www.pilatus-aircraft.com/en. You may 
view this referenced service information at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas City, 
MO 64106. For information on the availability of this material at the 
FAA, call (816) 329-4148. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0857.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0857; 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, any 
comments received, and other information. The 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, Aviation Safety 
Engineer, FAA, General Aviation & Rotorcraft Section, International 
Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; phone: 
(816) 329-4059; fax: (816) 329-4090; email: <a href="/cdn-cgi/l/email-protection#a6c2c9d3c188d4d3c2c9cad6cee6c0c7c788c1c9d0"><span class="__cf_email__" data-cfemail="d7b3b8a2b0f9a5a2b3b8bba7bf97b1b6b6f9b0b8a1">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2014-25-04, Amendment 39-18045 (79 FR 
73803, December 12, 2014) (AD 2014-25-04). AD 2014-25-04 applied to all 
Pilatus 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 resulted 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. AD 2014-25-04 required incorporating 
revised airworthiness limitations into the AMM for your FAA-approved 
maintenance program.
    The NPRM published in the Federal Register on October 2, 2020 (85 
FR 62266). The NPRM was prompted by a MCAI issued by the European Union 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Union. EASA superseded its previous MCAIs 
on this unsafe condition with EASA AD 2020-0120, dated May 27, 2020 
(EASA AD 2020-0120). The NPRM proposed to require revising the 
airworthiness limitation section of the existing maintenance manual or 
instructions for continued airworthiness to incorporate new 
airworthiness limitations, and performing an eddy current inspection of 
the fuselage wing fittings and wing to fuselage fittings.
    After the FAA issued the NPRM, EASA superseded EASA AD 2020-0120 
and issued EASA AD 2020-0278, dated December 14, 2020 (EASA AD 2020-
0278) (also referred to after this as ``the MCAI''). According to EASA 
AD 2020-0278, an installation procedure specified in the service 
information identified in the NPRM contained an error and, therefore, 
did not adequately address the identified unsafe condition. Pilatus 
revised the airworthiness limitations and issued corrected service 
information, which includes installing certain bushes using grease 
instead of a bonding agent and an additional one-time eddy current 
inspection of the fuselage wing fittings and wing-to-fuselage fittings 
if the last inspection was performed using an earlier version of the 
service information. You may examine the MCAI in the AD docket at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0857.
    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 to supersede AD 2014-25-04. The SNPRM published 
in the Federal Register on March 8, 2021 (86 FR 13222). The SNPRM 
proposed to add an eddy current inspection of each fuselage wing 
fitting if an earlier version of the service information was 
accomplished. The FAA is issuing this AD to address reduced airplane 
controllability due to possible loss of structural integrity of certain 
parts.

Discussion of the Final Airworthiness Directive

Comments

    The FAA received no comments on the SNPRM or on the determination 
of the costs.

Conclusion

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to the FAA's bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
and service information referenced above. The FAA reviewed the relevant 
data and determined that air safety requires adoption of the AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. This AD is adopted as proposed in the 
SNPRM.

Related Service Information Under 1 CFR Part 51

    Pilatus issued the Airworthiness Limitations Section of PC-6 
Airworthiness Limitations Document No. 02334, Revision 10, dated 
October 30, 2020; and Section 04-00-00, Airworthiness Limitations of 
Chapter 04, Airworthiness Limitations, of the Pilatus PC-6 Aircraft 
Maintenance Manual Document No. 01975, Revision 30, dated October 30, 
2020. This service information contains airworthiness limitations for 
the stabilizer trim actuator, fuselage wing fittings, and wing-to-
fuselage fittings. These documents are distinct since they apply to 
different airplane models.
    Pilatus also issued Section 53-00-01, Fuselage Wing Fittings--
Inspection/Check, of the Pilatus PC-6 Aircraft Maintenance Manual 
Document No. 01975, Revision 30, dated October 30, 2020; Section 57-00-
03, Wing to Fuselage Fittings--Inspection/Check, of the PC-6 Aircraft 
Maintenance Manual Document No. 01975, Revision 29, dated February 28, 
2020; Appendix K, Fuselage Wing Fittings--Inspection/Check, of the PC-6 
Airworthiness Limitations Document No. 02334, Revision 10, dated 
October 30, 2020; and Appendix L, Wing to Fuselage Fittings--
Inspection/Check, of the PC-6 Airworthiness Limitations Document No. 
02334, Revision 9, dated March 6, 2020. This service information 
specifies procedures for repetitive eddy current inspections of the 
fuselage wing fittings and wing-to-fuselage fittings and, if necessary, 
installing the bush on the fuselage wing fittings using grease. These 
documents are distinct since they apply to different airplane models.
    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 affects 30 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 30157]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
ALS revision.....................  1 work-hour x $85                $0  $85................  $2,550.
                                    per hour = $85.
Eddy current inspection of the     7 work-hours x $85            1,860  2,455 per            73,650 per
 fuselage wing fittings and         per hour = $595.                     inspection cycle.    inspection cycle.
 wing[dash]to[dash]fuselage
 fittings.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do the inspections and 
installation that would be required if an earlier version of the 
service information has been accomplished. The agency has no way of 
determining the number of aircraft that might need these inspections 
and installation:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Visual and eddy current inspection and          7 work-hours x $85 per hour =             $1,860          $2,455
 installation for certain bushes.                $595.
----------------------------------------------------------------------------------------------------------------

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 that 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.

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:
0
a. Removing Airworthiness Directive 2014-25-04, Amendment 39-18045 (79 
FR 73803, December 12, 2014), and
0
b. Adding the following new airworthiness directive:

2021-11-08 Pilatus Aircraft Ltd.: Amendment 39-21570; Docket No. 
FAA-2020-0857; Project Identifier MCAI-2020-00707-A.

(a) Effective Date

    This airworthiness directive (AD) is effective July 12, 2021.

(b) Affected ADs

    This AD replaces AD 2014-25-04, Amendment 39-18045 (79 FR 73803, 
December 12, 2014) (AD 2014-25-04).

(c) Applicability

    This AD applies to 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, 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 (ATA) of America Code 05, Time Limits/
Maintenance Checks.

(e) Reason

    This AD was prompted by a determination that new and more 
restrictive airworthiness limitations, new life limits, and new 
inspection procedures are necessary. The FAA is issuing this AD to 
address reduced airplane controllability due to possible loss of 
structural integrity of certain parts.

(f) Airworthiness Limitations Revision

    Unless already done, before further flight, comply with the 
actions specified in paragraphs (f)(1) through (3) of this AD.
    (1) For Models PC-6/B2-H2 and PC-6/B2-H4 airplanes, revise the 
airworthiness limitations section (ALS) of the existing maintenance 
manual or instructions for continued airworthiness (ICA) for your 
airplane as follows:
    (i) Replace Section 04-00-00 with Section 04-00-00, 
Airworthiness Limitations, of Chapter 04, Airworthiness Limitations, 
of the Pilatus PC-6 Aircraft Maintenance Manual Document No. 01975, 
Revision 30, dated October 30, 2020.
    (ii) Add (or replace, if applicable) Section 53-00-01, Fuselage 
Wing Fittings--Inspection/Check, of the Pilatus PC-6 Aircraft 
Maintenance Manual Document No. 01975, Revision 30, dated October 
30, 2020.
    (iii) Add Section 57-00-03, Wing to Fuselage Fittings--
Inspection/Check, of the Pilatus PC-6 Aircraft Maintenance Manual 
Document No. 01975, Revision 29, dated February 28, 2020.
    (2) For all airplanes specified in paragraph (c) of this AD 
except Models PC-6/B2-H2 and PC-6/B2-H4 airplanes, revise the ALS of

[[Page 30158]]

the existing maintenance manual or ICA for your airplane as follows:
    (i) Replace the ALS with the Airworthiness Limitations Section 
of Pilatus PC-6 Airworthiness Limitations Document No. 02334, 
Revision 10, dated October 30, 2020.
    (ii) Add (or replace, if applicable) Appendix K, Fuselage Wing 
Fittings--Inspection/Check, of Pilatus PC-6 Airworthiness 
Limitations Document No. 02334, Revision 10, dated October 30, 2020.
    (iii) Add Appendix L, Wing to Fuselage Fittings--Inspection/
Check, of Pilatus PC-6 Airworthiness Limitations Document No. 02334, 
Revision 9, dated March 6, 2020.
    (3) For all airplanes specified in paragraph (c) of this AD, 
after revising the ALS as required by paragraphs (f)(1) and (2) of 
this AD, remove from service each part that has reached or exceeded 
its new life limit.

(g) Inspections and Replacement

    (1) For airplanes with a bush part number (P/N) 6100.0020.01 
that has been bonded as specified in Section 53-00-01, Fuselage Wing 
Fittings--Inspection/Check, of Pilatus PC-6 Aircraft Maintenance 
Manual Document No. 01975, Revision 29, dated February 28, 2020; or 
Appendix K, Fuselage Wing Fittings--Inspection/Check, of Pilatus PC-
6 Airworthiness Limitations Document No. 02334, Revision 9, dated 
March 6, 2020: Within 50 hours time-in-service (TIS) after the 
effective date of this AD, perform a visual and eddy current 
inspection of each fuselage wing fitting on fuselage Frame 3, remove 
bush P/N 6100.0020.01 from service, and install a new (zero hours 
TIS) bush P/N 6100.0020.01 into Frame 3 with grease by using the 
procedures specified in paragraph (f)(1)(ii) or (f)(2)(ii) of this 
AD, as applicable to your airplane.
    (2) Unless already done, within 1,100 hours TIS after the 
effective date of this AD or within 12 months after the effective 
date of this AD, whichever occurs first, perform an eddy current 
inspection of each fuselage wing fitting and each wing-to-fuselage 
fitting using the procedures specified in paragraphs (f)(1)(ii) and 
(iii) of this AD, or paragraphs (f)(2)(ii) and (iii) of this AD, as 
applicable to your airplane. Thereafter, repeat the eddy current 
inspection of each fuselage wing fitting and each wing-to-fuselage 
fitting at the intervals specified in the ALS identified in 
paragraph (f)(1)(i) or (f)(2)(i), as applicable to your airplane.

(h) No Alternative Actions or Intervals

    After the ALS has been revised as required by paragraph (f) of 
this AD, no alternative inspection intervals or procedures may be 
approved, except as provided in paragraph (i) of this AD.

(i) Other FAA AD Provisions

    Alternative Methods of Compliance (AMOCs): The Manager, 
International Validation Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Send your request to the person identified in Related 
Information. Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspection, the manager 
of the local Flight Standards District Office.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Union Aviation Safety Agency (EASA) AD 2020-0120, 
dated May 27, 2020, and EASA AD 2020-0278, dated December 14, 2020, 
for related information. This MCAI may be found in the AD docket at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0857.
    (2) For more information about this AD, contact Doug Rudolph, 
Aviation Safety Engineer, FAA, General Aviation & Rotorcraft 
Section, International Validation Branch, 901 Locust, Room 301, 
Kansas City, MO 64106; telephone: (816) 329-4059; fax: (816) 329-
4090; email: <a href="/cdn-cgi/l/email-protection#88ece7fdefa6fafdece7e4f8e0c8eee9e9a6efe7fe"><span class="__cf_email__" data-cfemail="74101b01135a0601101b18041c341215155a131b02">[email protected]</span></a>.

(k) 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 this AD specifies otherwise.
    (i) Pilatus PC-6 Aircraft Maintenance Manual Document No. 01975, 
Revision 29, dated February 28, 2020.
    (A) Section 57-00-03, Wing to Fuselage Fittings--Inspection/
Check.
    (B) [Reserved]
    (ii) Pilatus PC-6 Aircraft Maintenance Manual Document No. 
01975, Revision 30, dated October 30, 2020.
    (A) Section 04-00-00, Airworthiness Limitations, of Chapter 04, 
Airworthiness Limitations.
    (B) Section 53-00-01, Fuselage Wing Fittings--Inspection/Check.
    (iii) Pilatus PC-6 Airworthiness Limitations Document No. 02334, 
Revision 9, dated March 6, 2020.
    (A) Appendix L, Wing to Fuselage Fittings--Inspection/Check.
    (B) [Reserved]
    (iv) Pilatus PC-6 Airworthiness Limitations Document No. 02334, 
Revision 10, dated October 30, 2020.
    (A) Airworthiness Limitations Section.
    (B) Appendix K, Fuselage Wing Fittings--Inspection/Check.
    (3) For service information identified in this AD, contact 
Pilatus Aircraft Ltd., Customer Support General Aviation, CH-6371 
Stans, Switzerland; telephone: +41 848 24 7 365; email: 
<a href="/cdn-cgi/l/email-protection#f2a697919a818782829d8086b2829b9e93868781939b809180939486dc919d9f"><span class="__cf_email__" data-cfemail="c490a1a7acb7b1b4b4abb6b084b4ada8a5b0b1b7a5adb6a7b6a5a2b0eaa7aba9">[email protected]</span></a>; website: https://www.pilatusaircraft.com/en.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 
Locust, Kansas City, MO 64106. For information on the availability 
of this material at the FAA, call (816) 329-4148.
    (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: <a href="/cdn-cgi/l/email-protection#610704051304064f0d0406000d210f0013004f060e17"><span class="__cf_email__" data-cfemail="bfd9dadbcddad891d3dad8ded3ffd1decdde91d8d0c9">[email protected]</span></a>, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on May 15, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-11812 Filed 6-4-21; 8:45 am]
BILLING CODE 4910-13-P


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