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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 Fair-
child Republic Company airplanes,  Fairchild Industries  airplanes,  Fair-
child Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 05,  Time Limits/Main-
    tenance Checks.

(e) REASON

    This AD was prompted  by a determination that new and more restrictive
    airworthiness limitations, new life limits,  and new inspection proce-
    dures 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 airworthi-
    ness 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 Limita-
    tions, 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 Fitt-
     ings - 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 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 revis-
    ing the ALS as required by paragraphs (f)(1) and (2)  of this AD,  re-
    move 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 - In-
    spection/Check,  of  Pilatus PC-6 Aircraft Maintenance Manual Document
    No. 01975, Revision 29, dated February 28, 2020;  or Appendix K, Fuse-
    lage Wing Fittings - Inspection/Check,  of  Pilatus PC-6 Airworthiness
    Limitations Document No. 02334, Revision 9, dated March 6, 2020: With-
    in 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,  Inter-
    national Validation Branch,  901 Locust,  Room  301,  Kansas City,  MO
    64106;  telephone: (816) 329-4059;  fax: (816) 329-4090;  email: doug.
    rudolph@faa.gov.

(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, Airworthi-
    ness 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 Air-
    craft Ltd., Customer Support General Aviation, CH-6371 Stans, Switzer-
    land; telephone: +41 848 24 7 365; email: Techsupport@pilatusaircraft.
    com; website: https://www.pilatusaircraft.com/en.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts 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 refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability  of  this  material  at  NARA,  email:
    fedreg.legal@nara.gov,  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.

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: doug.rudolph@faa.gov.
PREAMBLE 

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-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: doug.rudolph@faa.gov.

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:

Estimated Costs

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

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

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

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]

2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 2014-25-04, Amendment 39-18045 (79
FR 73803, December 12, 2014), and

b. Adding the following new airworthiness directive: