Rule2021-11812
Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
June 7, 2021
Effective
July 12, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
<html>
<head>
<title>Federal Register, Volume 86 Issue 107 (Monday, June 7, 2021)</title>
</head>
<body><pre>
[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-11812]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]]
<a href="http://aircraft.com">aircraft.com</a>; website: <a href="https://www.pilatus-aircraft.com/en">https://www.pilatus-aircraft.com/en</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2020-
0857.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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
<a href="https://www.regulations.gov">https://www.regulations.gov</a> 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
<a href="https://www.regulations.gov">https://www.regulations.gov</a> 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: <a href="https://www.pilatusaircraft.com/en">https://www.pilatusaircraft.com/en</a>.
(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: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
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
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on June 7, 2021.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.