[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:
[email protected]
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:
[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.
(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]
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