[Federal Register Volume 85, Number 192 (Friday, October 2, 2020)]
[Proposed Rules]
[Pages 62266-62269]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-21794]


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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]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Limited Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2014-25-04, which applies to all Pilatus Aircraft Limited (Pilatus) 
Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-
6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-
H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. AD 2014-25-04 requires 
incorporating revised airworthiness limitations into the aircraft 
maintenance manual (AMM). Since the FAA issued AD 2014-25-04, the FAA 
has determined that new or more restrictive airworthiness limitations 
are necessary for the stabilizer trim actuator, fuselage wing fittings, 
and wing-to-fuselage fittings. This proposed AD would 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. The FAA is 
proposing

[[Page 62267]]

this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by November 
16, 2020.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Pilatus 
Aircraft Ltd., Customer Support General Aviation, CH-6371 Stans, 
Switzerland; telephone: +41 848 24 7 365; email: aircraft.com">Techsupport@pilatus-aircraft.com; internet: https://www.pilatus-aircraft.com/en. You may 
view this 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.

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-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 NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
General Aviation & Rotorcraft Section, International Validation Branch, 
901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 
329-4059; fax: (816) 329-4090; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2020-0857; 
Project Identifier MCAI-2020-00707-A'' at the beginning of your 
comments. The most helpful comments reference a specific portion of the 
proposal, explain the reason for any recommended change, and include 
supporting data. The FAA will consider all comments received by the 
closing date and may amend this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposal.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Doug 
Rudolph, Aerospace Engineer, FAA, General Aviation & Rotorcraft 
Section, International Validation Branch, 901 Locust, Room 301, Kansas 
City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; 
email: [email protected]. Any commentary that the FAA receives which 
is not specifically designated as CBI will be placed in the public 
docket for this rulemaking.

Discussion

    The FAA issued AD 2014-25-04, Amendment 39-18045 (79 FR 73803, 
December 12, 2014) (``AD 2014-25-04''), for all Pilatus Models PC-6, 
PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-
H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-
H2, and PC-6/C1-H2 airplanes. AD 2014-25-04 requires incorporating 
revised airworthiness limitations into the AMM for your FAA-approved 
maintenance program. AD 2014-25-04 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. The FAA issued AD 2014-25-04 to address new life 
limits for the fire extinguisher, which are required to ensure the 
continued operational safety of the affected airplanes.

Actions Since AD 2014-25-04 Was Issued

    Since the FAA issued AD 2014-25-04, the European Union Aviation 
Safety Agency (EASA), which is the Technical Agent for the Member 
States of the European Union, superseded its MCAI and issued EASA AD 
No. 2018-0285, dated December 20, 2018, which was superseded with EASA 
AD No. 2020-0120, dated May 27, 2020 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''). The 
MCAI corrects an unsafe condition for all Pilatus Models PC-6, PC-6-H1, 
PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-
H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/
C1-H2 airplanes. The MCAI states that Pilatus has revised the 
airworthiness limitations section for the subject airplanes to 
introduce new data modules for two existing mandatory inspection tasks, 
the inspection of fuselage wing fittings and the inspection of wing to 
fuselage fittings. According to EASA, the new data modules require non-
destructive visual and eddy current inspections in place of the 
previous requirement for a fluorescent dye-penetrant method.
    You may examine the MCAI in the AD docket on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0857.
    The FAA has determined that new and more restrictive airworthiness 
limitations, new life limits, and new inspection procedures are 
necessary, including for the stabilizer trim actuator and attachments, 
fuselage wing fittings, and wing-to-fuselage fittings. The FAA is 
proposing this AD to address reduced airplane controllability due to 
possible loss of structural integrity of certain parts.

Related Service Information Under 1 CFR Part 51

    Pilatus has issued PC-6 Airworthiness Limitations Document Number 
02334, Revision 9, dated March 6, 2020; and Section 04-00-00, 
Airworthiness Limitations of Chapter 04, Airworthiness Limitations, of 
the Pilatus PC-6 Aircraft Maintenance

[[Page 62268]]

Manual Document Number 01975, Revision 29, dated February 28, 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, Chapter 53, Fuselage, and 
Section 57-00-03, Chapter 57, Wings, of the Pilatus PC-6 Aircraft 
Maintenance Manual Document Number 01975, Revision 29, dated February 
28, 2020; and Appendix K and Appendix L of PC-6 Airworthiness 
Limitations Document Number 02334, Revision 9, dated March 6, 2020. 
This service information contains procedures for repetitive eddy 
current inspections of the fuselage wing fittings and wing-to-fuselage 
fittings.
    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.

FAA's Determination

    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 is proposing this AD 
because the FAA evaluated all the relevant information and determined 
the unsafe condition described previously is likely to exist or develop 
on other products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would retain none of the requirements of AD 2014-
25-04. This proposed AD would require revising the airworthiness 
limitation section of the existing maintenance manual or instructions 
for continued airworthiness to incorporate new airworthiness 
limitations. The revised limitations include an eddy current inspection 
of the fuselage wing fittings and wing-to-fuselage fittings. This 
proposed AD would also require performing the eddy current inspection 
of the fuselage wing fittings and wing-to-fuselage fittings first 
within 1,100 hours time-in-service or 12 months, and thereafter at the 
intervals specified in the revised limitations.
    This proposed AD would require revisions to the airworthiness 
limitations section of an operator's maintenance documents to include 
new inspections. Compliance with the airworthiness limitations section 
is required by 14 CFR 91.403(c).

Costs of Compliance

    The FAA estimates that this proposed AD would affect 30 airplanes 
of U.S. registry. The FAA also estimates that it would take about 1 
work-hour per product to comply with the basic requirements 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 would be $2,550, or $85 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    (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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 (AD) 2014-25-04, Amendment 39-18045 
(79 FR 73803, December 12, 2014); and
0
b. Adding the following new AD:

Pilatus Aircraft Limited: Docket No. FAA-2020-0857; Project 
Identifier MCAI-2020-00707-A.

(a) Comments Due Date

    The FAA must receive comments by November 16, 2020.

(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 Limited Models PC-6, PC-6-
H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, 
PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, 
and PC-6/C1-H2 airplanes, all 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

[[Page 62269]]

Pilatus PC-6 Aircraft Maintenance Manual Document Number 01975, 
Revision 29, dated February 28, 2020.
    (ii) Add Section 53-00-01, Chapter 53, Fuselage, of the Pilatus 
PC-6 Aircraft Maintenance Manual Document Number 01975, Revision 29, 
dated February 28, 2020.
    (iii) Add Section 57-00-03, Chapter 57, Wings, of the Pilatus 
PC-6 Aircraft Maintenance Manual Document Number 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 
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 Number 02334, 
Revision 9, dated March 6, 2020.
    (ii) Add Appendix K of Pilatus PC-6 Airworthiness Limitations 
Document Number 02334, Revision 9, dated March 6, 2020.
    (iii) Add Appendix L of Pilatus PC-6 Airworthiness Limitations 
Document Number 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) One-Time Eddy Current Inspection

    Unless already done, within 1,100 hours time-in-service 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 information to Doug Rudolph, Aerospace Engineer, FAA, 
General Aviation & Rotorcraft Section, International Validation 
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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Union Aviation Safety Agency (EASA) AD No. 2018-
0285, dated December 20, 2018, and EASA AD No. 2020-0120, dated May 
27, 2020, for related information. This MCAI may be found in the AD 
docket on the internet 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, 
Aerospace Engineer, FAA, General Aviation & Rotorcraft Section, 
International Validation Branch, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; 
email: [email protected].
    (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: 
aircraft.com">Techsupport@pilatus-aircraft.com; internet: https://www.pilatus-aircraft.com/en. You may view this 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.

    Issued on September 25, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-21794 Filed 10-1-20; 8:45 am]
BILLING CODE 4910-13-P