
[Federal Register Volume 81, Number 214 (Friday, November 4, 2016)]
[Rules and Regulations]
[Pages 76845-76848]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26431]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9356; Directorate Identifier 2016-CE-033-AD; 
Amendment 39-18701; AD 2016-22-12]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Pilatus Aircraft Ltd. 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. This 
AD results from mandatory continuing airworthiness information (MCAI) 
issued by the aviation authority of another country to identify and 
correct an unsafe condition on an aviation product. The MCAI describes 
the unsafe condition as wear and cracks on the stabilizer-trim 
attachment and structural components. We are issuing this AD to require 
actions to address the unsafe condition on these products.

[[Page 76846]]


DATES: This AD is effective November 4, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 4, 
2016.
    We must receive comments on this AD by December 19, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Pilatus 
Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland; 
telephone: +41 41 619 3333; fax: +41 41 619 7311; Internet: http://www.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. It is also available on the 
Internet at http://www.regulations.gov by searching for locating Docket 
No. FAA-2016-9356.

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-2016-
9356; 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 this AD, 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.

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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued 
Emergency AD No. 2016-0202-E, dated October 7, 2016 (referred to after 
this as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Wear and cracks on the stabilizer-trim attachment and relevant 
structural components have been reported on aeroplanes having 
accomplished Pilatus Service Bulletin (SB) 53-001 Revision 1, as 
previously required by FOCA AD HB-2005-263.
    Subsequent investigation identified that slightly asymmetric 
installation and/or operational conditions may result in strong 
stabilizer vibration, causing crack initiation in the stabilizer-
trim attachment fitting or connecting piece.
    This condition, if not detected and corrected, may lead to a 
failure of the fitting or connecting piece, possibly resulting in 
disconnection of the horizontal stabilizer rear attachment, with 
consequent loss of control of the aeroplane.
    To address this potential unsafe condition, Pilatus issued SB 
No. 53-003 (hereafter referred to as `the SB' in this AD) to provide 
inspection instructions.
    For the reason described above, this AD requires visual and non 
destructive inspections of the affected stabilizer-trim attachment 
components and the related parts and structure to detect cracks, 
and, depending on findings, the replacement of the affected parts. 
This AD also provides additional requirements for installation of 
these parts.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-9356.

Related Service Information Under 1 CFR Part 51

    Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 53-003, 
Revision 1, dated October 13, 2016. The service information describes 
procedures for inspecting the stabilizer-trim attachment components and 
the related parts and structure to detect cracks and replacing all 
cracked parts. 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 of this 
AD.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are issuing this AD because we 
evaluated all information provided by the State of Design Authority and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
failure of the stabilizer control system fitting or connecting piece 
could result in disconnection of the horizontal stabilizer rear 
attachment, with consequent loss of control. Therefore, we determined 
that notice and opportunity for public comment before issuing this AD 
are impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2016-9356; Directorate 
Identifier 2016-CE-033-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD will affect 30 products of U.S. registry. 
We also estimate that it will take about 5 work-hours per product to 
comply with the basic inspection requirements of this AD. The average 
labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $12,750, or $425 per product.
    In addition, we estimate that any necessary follow-on replacement 
actions will take about 6 work-hours and

[[Page 76847]]

require parts costing $2,000, for a cost of $2,510 per product. We have 
no way of determining the number of products that may need these 
actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave., SW., Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

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 that 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.

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

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 adding the following new AD:

2016-22-12 Pilatus Aircraft Ltd.: Amendment 39-18701; Docket No. 
FAA-2016-9356; Directorate Identifier 2016-CE-033-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective November 4, 
2016.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to 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, all manufacturer serial numbers, including MSN 2001 
through 2092 (see Note 1 of paragraph c), certificated in any 
category.

    Note 1 of paragraph (c):  For MSN 2001-2092, these airplanes are 
also identified as Fairchild Republic Company PC-6 airplanes, 
Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 
airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.

    (2) For the purpose of this AD, an ``affected part'' is any 
stabilizer-trim attachment component and the related parts and 
structure, as identified in Pilatus Aircraft Ltd. (Pilatus) PC-6 
Service Bulletin (SB) No. 53-003, Revision 1, dated October 13, 
2016.

(d) Subject

    Air Transport Association of America (ATA) Code 53: Fuselage.

(e) Reason

    This AD results from mandatory continuing airworthiness 
information (MCAI) issued by the aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as wear and cracks 
on the stabilizer-trim attachment and structural components. This 
condition, if not corrected, could cause failure of the stabilizer 
control system fitting or connecting piece, which could result in 
disconnection of the horizontal stabilizer rear attachment with 
consequent loss of control.

(f) Actions and Compliance

    Unless already done, do the following actions.
    (1) For MSN 337 through 1005 and 2001 through 2092: Before 
further flight after November 4, 2016 (the effective date of this 
AD), do a visual inspection of the affected stabilizer-trim 
attachment and structural components following the Accomplishment 
Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated 
October 13, 2016.
    (2) For MSN 337 through 1005 and 2001 through 2092: Within the 
next 100 hours time-in-service after November 4, 2016 (the effective 
date of this AD), do a visual inspection and dye-penetrant or eddy 
current inspection of the affected stabilizer-trim attachment and 
structural components following the Accomplishment Instructions in 
Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016.
    (3) For MSN 337 through 1005 and 2001 through 2092: If any crack 
is found during any inspection required by paragraphs (f)(1) and (2) 
of this AD, before further flight, replace the affected part with a 
serviceable part following the Accomplishment Instructions in 
Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. For 
the purpose of this AD, a ``serviceable part'' is an affected part 
that is new, or has passed an inspection before installation 
following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-
003, Revision 1, dated October 13, 2016.
    (4) For MSN 337 through 1005 and 2001 through 2092: Within 10 
days after the inspections required by paragraphs (f)(1) and (2) of 
this AD or within the next 10 days after the effective date of this 
AD, whichever occurs later, report the results to Pilatus at the 
address in paragraph (j)(3) of this AD using the Report Form in 
Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016.
    (5) For all affected MSNs: As of November 4, 2016 (the effective 
date of this AD), an affected part listed in Pilatus PC-6 SB No. 53-
003, Revision 1, dated October 13, 2016, may be installed provided 
it is a serviceable part. For the purpose of this AD, a 
``serviceable part'' is an affected part that is new, or has passed 
an inspection before installation following the Accomplishment 
Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated 
October 13, 2016.

(g) Credit for Actions Done Following Previous Service Information

    This AD allows credit for the visual inspection required in 
paragraph (f)(1) of this

[[Page 76848]]

AD if done before November 4, 2016 (the effective date of this AD), 
following Pilatus PC-6 SB No. 53-003, dated October 4, 2016. The 
dye-penetrant or eddy current inspection must still be done 
following Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 
2016.

(h) 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 requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: 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. 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.
    (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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, a federal agency may not conduct or sponsor, and a person 
is not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(i) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2016-0202-E, dated October 7, 2016, and Pilatus Aircraft Ltd. PC-6 
Service Bulletin No. 53-003, dated October 4, 2016. You may examine 
the MCAI on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9356.

(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 this AD specifies otherwise.
    (i) Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 53-003, 
Revision 1, dated October 13, 2016.
    (ii) Reserved.
    (3) For Pilatus Aircraft Ltd. service information identified in 
this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, 
CH-6371 STANS, Switzerland; telephone: +41 41 619 3333; fax: +41 41 
619 7311; Internet: http://www.pilatus-aircraft.com.
    (4) You may view this service information at the FAA, 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. It is also available on the Internet at http://www.regulations.gov by searching for locating Docket No. FAA-2016-
9356.
    (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 27, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-26431 Filed 11-3-16; 8:45 am]
 BILLING CODE 4910-13-P


