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2014-22-01 PILATUS AIRCRAFT LTD.:
Amendment 39-18005; Docket No. FAA-2014-0594; Directorate Identifier 2014-CE-022-AD.

(a) EFFECTIVE DATE

    This airworthiness directive (AD) becomes effective December 18, 2014.

(b) AFFECTED ADS

    This AD  supersedes AD  2012-26-16,  Amendment  39-17311 (78 FR 11572,
    February 19, 2013).

(c) APPLICABILITY

    This AD applies  to PILATUS AIRCRAFT  LTD. Models PC-12,  PC-12/45, PC
    -12/47,  and  PC-12/47E  airplanes,  all  manufacturer  serial numbers
    (MSNs), certificated in any category.

(d) SUBJECT

    Air Transport Association of America (ATA) Code 5: Time Limits.

(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  a  need to  incorporate new
    revisions into the Limitations section, Chapter 4, of the FAA-approved
    maintenance program (e.g.,  maintenance manual). The  limitations were
    revised to include  repetitive inspections of  the inboard flap  drive
    arms for crack(s). These actions are required to ensure the  continued
    operational safety of the affected airplanes.

(f) ACTIONS AND COMPLIANCE

    Unless  already  done, do  the  actions in  paragraphs  (f)(1) through
    (f)(5) of this AD:

(1) Before further flight  after  December 18, 2014 (the effective date of
    this   AD),   insert   Data   module   code  12-A-04-00-00-00A-000A-A,
    "STRUCTURAL, COMPONENT AND MISCELLANEOUS – AIRWORTHINESS LIMITATIONS,"
    dated March 13, 2014, of the Pilatus Model type – PC-12, PC-12/45,  PC
    -12/47, Aircraft  Maintenance Manual  (AMM), Document  No. 02049, 12-A
    -AM-00-00-00-I, revision 28, dated May 31, 2014, for Models PC-12,  PC
    -12/45,  PC-12/47,  and  Data  module  code  12-B-04-00-00-00A-000A-A,
    "STRUCTURAL AND  COMPONENT LIMITATIONS  – AIRWORTHINESS  LIMITATIONS,"
    dated March 13, 2014, of  the Pilatus Model type –  PC-12/47E MSN-1001
    -UP, Aircraft  Maintenance Manual  (AMM), Document  No. 02300, 12-B-AM
    -00-00-00-I, revision  11, dated  May 31,  2014, for  Model PC-12/47E,
    into the Limitations section  of the FAA-approved maintenance  program
    (e.g., maintenance manual). These limitations section revisions do the
    following:

(i) Establish an inspection of the inboard flap drive arms,

(ii) Specify  replacement  of  components  before  or  upon  reaching  the
     applicable life limit, and

(iii) Specify  accomplishment  of  all applicable maintenance tasks within
      certain thresholds and intervals.

(2) Only  authorized  Pilatus  Service  Centers  can  do  the Supplemental
    Structural Inspection Document (SSID) as required by the documents  in
    paragraph (f)(1) of this AD because deviations from the type design in
    critical locations could  make the airplane  ineligible for this  life
    extension.

(3) If  no  compliance  time  is  specified  in  the  documents  listed in
    paragraph (f)(1) of  this AD when  doing any corrective  actions where
    discrepancies are found as  required in paragraph (f)(1)(iii)  of this
    AD, do these corrective actions before further flight after doing  the
    applicable maintenance task.

(4) During the accomplishment of the actions required in paragraphs (f)(1)
    (i), (f)(1)(ii), and (f)(1)(iii) of this AD, if a discrepancy is found
    that is not identified in the  documents listed in paragraph (f)(1) of
    this AD,  before further flight after finding the discrepancy, contact
    PILATUS AIRCRAFT LTD at the address specified in paragraph (i) of this
    AD for a repair scheme and incorporate that repair scheme.

(5) Within the next 3 months  after  December 18, 2014 (the effective date
    of this AD) or within the  next 150 hours TIS after  December 18, 2014
    (the effective date of this  AD), whichever occurs first, inspect  the
    inboard flap drive arms for  cracks and take all necessary  corrective
    actions.

(g) OTHER FAA AD PROVISIONS

    The following provisions also apply to this AD:

(1) Alternative  Methods  of Compliance (AMOCs):  The  Manager,  Standards
    Office,  FAA,  has the authority to approve AMOCs for this AD,  if re-
    quested using the procedures found in 14 CFR 39.19.  Send  information
    to Doug Rudolph, Aerospace Engineer, FAA,  Small Airplane Directorate,
    901 Locust,  Room 301,  Kansas City, Missouri 64106;  telephone: (816)
    329-4059; fax: (816) 329-4090; email: doug.rudolph@faa.gov.

(i) 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.

(ii) AMOCs approved  for  AD 2012-26-16,  Amendment 39-17311 (77 FR 11572,
     February 19, 2013) are not approved as AMOCs for this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective
    actions from a manufacturer or other source, use these actions if they
    are FAA-approved.  Corrective actions  are considered  FAA-approved if
    they are approved by the State of Design Authority (or their delegated
    agent). You are required to assure the product is airworthy before  it
    is returned to service.

(h) SPECIAL FLIGHT PERMIT

    Special flight permits are prohibited.

(i) RELATED INFORMATION

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2014-0170,
    dated July 17, 2014, for related information. The MCAI can be found in
    the AD docket on the Internet at http://www.regulations.gov/#!document
    Detail; D=FAA-2014-0594-0003.

(j) 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) Data module code 12-A-04-00-00-00A-000A-A,  "STRUCTURAL, COMPONENT AND
    MISCELLANEOUS – AIRWORTHINESS LIMITATIONS,"  dated March 13, 2014,  of
    the  Pilatus  Model  type   –  PC-12,  PC-12/45,  PC-12/47,   Aircraft
    Maintenance  Manual  (AMM),  Document  No.  02049, 12-A-AM-00-00-00-I,
    revision 28, dated May 31, 2014.

(ii) Data module code 12-B-04-00-00-00A-000A-A,  "STRUCTURAL AND COMPONENT
     LIMITATIONS – AIRWORTHINESS LIMITATIONS" dated March 13, 2014, of the
     Pilatus  Model  type  –  PC-12/47E MSN-1001-UP,  Aircraft Maintenance
     Manual (AMM),  Document No. 02300,  12-B-AM-00-00-00-I,  revision 11,
     dated May 31, 2014.

Note  to  paragraph (j)(2) of this AD: Data module code 12-A-04-00-00-00A-
000A-A,  "STRUCTURAL,  COMPONENT AND MISCELLANEOUS – AIRWORTHINESS LIMITA-
TIONS," dated March 13, 2014, of the Pilatus Model type – PC-12, PC-12/45,
PC-12/47, Aircraft Maintenance Manual (AMM),  Document No. 02049, 12-A-AM-
00-00-00-I, revision 28, dated May 31, 2014; and Data module code 12-B-04-
00-00-00A-000A-A,  "STRUCTURAL  AND  COMPONENT LIMITATIONS – AIRWORTHINESS
LIMITATIONS," dated March 13, 2014,  of the Pilatus Model type – PC-12/47E
MSN-1001-UP, Aircraft Maintenance Manual (AMM),  Document No. 02300, 12-B-
AM-00-00-00-I,  revision 11,  dated May 31, 2014,  were issued as complete
updates to the AMM Airworthiness Limitations sections.

(3) For Pilatus Aircraft LTD. service information identified  in  this AD,
    contact PILATUS AIRCRAFT LTD, Customer Service Manager, CH-6371 STANS,
    Switzerland;  telephone: +41 (0) 41 619 33 33;  fax: +41 (0) 41 619 73
    11;  Internet:  http://www.pilatus-aircraft.com or email: SupportPC12@
    pilatus-aircraft.com.

(4) You  may  view  this  service  information  at  FAA,   Small  Airplane
    Directorate, 901 Locust, Kansas City, Missouri 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,  call
    202-741-6030,  or go to: http://www.archives.gov/federal-register/cfr/
    ibr-locations.html

Issued in Kansas City, Missouri, on October 20, 2014. Derek Morgan, Acting
Manager, Small Airplane Directorate, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph,  Aerospace  Engineer,  FAA,
Small Airplane Directorate,  901 Locust,  Room 301, Kansas City,  Missouri
64106; telephone: (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-2014-0594; Directorate Identifier 2014-CE-022-AD;
Amendment 39-18005; AD 2014-22-01]
RIN 2120-AA64

Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-26-16 for
all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/
47E 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 a need to incorporate new
revisions into the Limitations section, Chapter 4, of the FAA-approved
maintenance program (e.g., maintenance manual). We are issuing this AD
to require actions to address the unsafe condition on these products.

DATES: This AD is effective December 18, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 18,
2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.
regulations.gov by searching for and locating Docket No. FAA-2014-
0594; or in person at the Docket Management Facility, 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 service information identified in this AD, contact PILATUS
AIRCRAFT LTD., Customer Service Manager, CH-6371 STANS, Switzerland;
telephone: +41 (0) 41 619 33 33; fax: +41 (0) 41 619 73 11; Internet:
http://www.pilatus-aircraft.com or email: aircraft.com">SupportPC12@pilatus-
aircraft.com. You may view this referenced service information at the
FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the FAA,
call (816) 329-4148.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to add an AD that would apply to all PILATUS AIRCRAFT LTD.
Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. That NPRM
was published in the Federal Register on August 18, 2014 (79 FR 48701),
and proposed to supersede AD 2012-26-16, Amendment 39-17311 (78 FR
11572, February 19, 2013).
Since we issued AD 2012-26-16, Amendment 39-17311 (78 FR 11572,
February 19, 2013), PILATUS AIRCRAFT LTD. has issued revisions to the
Limitations section of the airplane maintenance manual to include
repetitive inspections of the inboard flap drive arms for cracks.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2014-0170, dated July 17, 2014 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:

The maintenance instructions and airworthiness limitations
applicable to the Structure and Components of PC-12 aeroplanes are
specified in the Aircraft Maintenance Manual (AMM) under Chapter 4,
Airworthiness Limitation Section (ALS).
The instructions contained in the ALS document have been
identified as mandatory actions for continued airworthiness and
failure to comply with these instructions and limitations could
potentially lead to an unsafe condition.
Pilatus Aircraft Ltd. recently issued Pilatus PC-12 AMM report
02049 issue 28 for PC-12, PC-12/45 and PC-12/47 aeroplanes and PC-12
AMM report 02300 issue 11 for PC-12/47E aeroplanes to incorporate
new repetitive inspection intervals of the inboard flap drive arms
because of the detection of cracked parts.
For the reason described above, this AD retains the requirements
of EASA AD 2013-0031, which is superseded, and requires
implementation of the new maintenance requirements and/or
airworthiness limitations.

The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2014-0594-0003.

Comments

We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.

Request To Remove Actions Retained From AD 2012-26-16, Amendment 39-
17311 (78 FR 11572, February 19, 2013) (``AD 2012-26-16'')


Johan Kruger, Pilatus Aircraft Ltd., requested that we remove the
actions retained from AD 2012-26-16, paragraphs (f)(1) and (f)(2) of
the proposed AD from the final rule AD action. These actions were
originally in AD 2009-14-13, Amendment 39-15963 (74 FR 34213, July 15,
2009), which was superseded by AD 2012-26-16.
Johan Kruger stated that the need to retain the actions previously
required in AD 2012-26-16, paragraphs (f)(1) and (f)(2) of the proposed
AD, no longer exists for the following reasons:
In AD 2012-26-16, the initial compliance time for
replacing the nose landing gear (NLG) torque tubes part number (P/N)
532.50.12.047 on Models PC-12 and PC-12/45 airplanes is within the next
100 hours time-in-service (TIS) after August 19, 2009 (the effective
date retained from AD 2009-14-13) or 1 year after August 19, 2009,
whichever occurs first. Compliance with this requirement should have
been completed by September 20, 2010. AD 2012-26-16 also prohibits
installing any NLG torque tube P/N 532.50.12.047 as of March 26, 2013
(the effective date retained from AD 2012-26-16).
Even if P/N 532.50.12.047 had not been replaced as
required in AD 2012-26-16, the life limit for P/N 532.50.12.047 in the
airworthiness limitations section (ALS) of the airplane maintenance
manual (AMM) referenced in the proposed AD is deemed adequate to
address the potential unsafe condition.
Since August 19, 2009, the effective date of AD 2009-14-
13, Pilatus has not provided any P/N 532.50.12.047 as spares to any
owners/operators in the United States. Pilatus is implying that
after the issuance of AD 2009-14-13, NLG torque tube P/N 532.50.12.047
has not been installed as a spare on any affected Model PC-12 and PC-
12/45 airplane in the United States.
Johan Kruger clarified that the unsafe condition caused by NLG
torque tube P/N 532.50.12.047 that was addressed in AD 2012-26-16,
which was a carryover from AD 2009-14-13, has sufficiently been
addressed and is now covered by the ALS of the AMM that is referenced
in the proposed AD, which is unchanged from AD 2012-26-16.
We agree with the commenter. We have changed the final rule AD
action based on this comment and have removed paragraphs (f)(1) and
(f)(2) as presented in the proposed AD from this final rule AD action.
Any airplane that has not operated since the torque tube requirement
was initiated through AD 2009-14-13 may apply for an alternative method
of compliance.

Request To Remove the Effective Date Imposed in the Proposed AD

Johan Kruger, Pilatus Aircraft Ltd., and Gerard Terpstra requested
that the effective date imposed in paragraph (f)(3) of the proposed AD
be removed.
The commenters stated that it is out of the ordinary to have a
compliance effective date imposed in a proposed AD. The commenters also
pointed out that the effective date is before the comment close date.
We agree with the commenters that compliance effective dates are
not normally put in a proposed AD. The September 22, 2014, effective
date in paragraph (f)(3) of the proposed AD was a mistake. There will
be no enforcement for that date in the final rule AD action and
comments were still allowed through the comment close date of October
6, 2014, before final rule action was taken.
We changed the final rule AD action based on these comments.

Request To Withdraw the Proposed AD

Gerard Terpstra requested that the proposed AD be withdrawn because
compliance with the new airworthiness limitations is already mandatory
under federal regulations.
Gerard Terpstra stated that Title 14 of the Code of Federal
Regulations (CFR), part 23, Appendix G, makes the requirements in the
ALS of the AMM mandatory and 14 CFR 91.403 additionally prohibits the
operation of an airplane unless the requirements of the ALS of the AMM
are complied with. Therefore, 14 CFR 39.5 cannot be the basis for
issuing the proposed AD because no unsafe condition exists.
Gerard Terpstra also stated that by using 14 CFR part 39 here the
FAA has in fact induced an unintended consequence of allowing an
operator to delay the implementation of the new ALS requirements. For
example, the FAA publishes an AD periodically to require compliance
with the then ``current'' version of the ALS of the Pilatus PC-12 AMM,
most recently with AD 2012-26-16, which became effective on March 26,
2013. Pilatus Aircraft Ltd. subsequently revised the ALS of the AMM by
publishing two temporary revisions on March 13, 2014. Gerard Terpstra
estimated the compliance date for the final rule AD action to be around
the first week of November 2014 (if the FAA observes the 45-day comment
period and the 35 days for complying with the AD after it becomes
effective). Between the time that Pilatus Aircraft Ltd. published their
temporary revision and the time the proposed AD becomes effective as a
final rule AD action is approximately six months, thereby delaying
compliance with the ALS by around six months.
Gerard Terpstra stated his understanding of the desire and
requirement to have regulations harmonized between different countries
and that is what is being done here. EASA issues an AD and the FAA
follows suit and issues an AD. But in this instance the proposed AD is
not required as the proper and appropriate Federal regulations are
already in place to ensure that the ALS of the AMM are complied with.
We don't agree with the commenter. Based on guidance from the FAA's
Office of the Chief Counsel (AGC), the definition of the word
``current'' is the ALS of the AMM that was delivered with the original
airworthiness (A/W) certificate of each airplane. The only way the FAA
can enforce the use of a newer version of the ALS to the AMM on the
entire existing fleet is through 14 CFR part 39 AD action.
We agree that the new ALS to the AMM is binding for a new airplane
upon the issuance of the A/W certificate or existing airplanes that
have the requirement as part of their operational specifications (e.g.,
14 CFR part 135 operations), but not for the entire existing fleet
(e.g., 14 CFR part 91 operations). EASA is in agreement with the FAA
and understands that the only way to require the most recent revision
to the ALS section for existing fleets in either state of registry
system is through AD action.

Conclusion

We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 48701, August 18, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 48701, August 18, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

We estimate that this AD will affect 770 products of U.S. registry.
We also estimate that it will take about 16.5 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $300 per product.
Based on these figures, we estimate the cost of this AD on U.S.
operators to be $1,310,925, or $1,702.50 per product. This breaks down
as follows:
New inspections, etc. through incorporating maintenance
manual limitations: 3.5 work-hours with parts about $300 for a fleet
cost of $460,075, or $597.50 per product.
Wing main spar fastener holes inspection: 12 work-hours
with no parts cost for fleet cost of $785,400 or $1,020 per product.
Inboard flap drive arm inspection: 1 work-hour with no
parts cost for fleet cost of $65,450 or $85 per product.
In addition, we estimate that any necessary corrective actions (on-
condition costs) that must be taken based on the above inspections,
etc. will take about 16 work-hours and require parts costing
approximately $10,000 for a cost of $11,360 per product. We have no way
of determining the number of products that may need these necessary
corrective actions. This breaks down as follows:
Replacements based on damaged parts or reduced life limits
as a result of the new maintenance manual limitations: 6 work-hours
with parts about $4,000 for a cost of $4,510 per product.
Repairs to the wing spar as a result of the wing main spar
fastener holes inspection: 7 work-hours with parts about $5,000 for a
cost of $5,595 per product.
Replacement of the inboard flap drive arm as a result of
the inboard flap drive arm inspection: 3 work-hours with parts about
$1,000 for a cost of $1,255.

The only costs that will be imposed by this AD over that already
required by AD 2012-26-16 is the inboard flap arm inspection and
replacement as necessary and the addition of 92 airplanes from 678
airplanes to 770 airplanes.

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.
We are 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

We 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) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2014-
0594; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains the NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

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

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 removing Amendment 39-17311 (78 FR
11572, February 19, 2013), and adding the following new AD: