Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 76845-76848 [2016-26431]
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Federal Register / Vol. 81, No. 214 / Friday, November 4, 2016 / Rules and Regulations
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
installed: Modify the stall warning and
identification system, in accordance with the
Accomplishment Instructions of Saab Service
Bulletin 340–27–109, dated April 14, 2014.
(e) Reason
This AD was prompted by a determination
that airplanes with certain modifications
were excluded from the applicability in AD
2012–24–06, and are affected by the
identified unsafe condition; and the stall
warning computer (SWC) required by AD
2012–24–06 contained erroneous logic. We
are issuing this AD to prevent natural stall
events during operation in icing conditions,
which could result in loss of control of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Deactivation of Stall Speed Curves
For airplanes identified in paragraphs
(g)(1) and (g)(2) of this AD: Within 30 days
after the effective date of this AD, do the
deactivation specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable to airplane
configuration, in accordance with the
Accomplishment Instructions of Saab Service
Bulletin 340–27–116, dated October 18, 2013.
(1) For airplanes with a basic wing tip that
has been modified using Saab Service
Bulletin 340–27–098: Deactivate the stall
speed curves in the SWC having part number
(P/N) 0020AK6.
(2) For airplanes with an extended wing tip
that has been modified using Saab Service
Bulletin 340–27–099: Deactivate the stall
speed curves in the SWC having P/N
0020AK7.
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(h) Replacement of SWCs
Within 3 months after the effective date of
this AD: Do the replacement specified in
paragraph (h)(1) or (h)(2) of this AD, as
applicable.
(1) For airplanes with basic wing tips:
Replace all SWCs with new, improved SWCs
having P/N 0020AK6–1, in accordance with
the Accomplishment Instructions of Saab
Service Bulletin 340–27–121, dated July 11,
2014.
(2) For airplanes with extended wing tips:
Replace all SWCs with new, improved SWCs
having P/N 0020AK7–1, in accordance with
the Accomplishment Instructions of Saab
Service Bulletin 340–27–122, dated July 11,
2014.
(i) Concurrent Modification
Before or concurrently with the
accomplishment of the applicable
requirements of paragraph (h) of this AD, do
the actions specified in paragraph (i)(1) or
(i)(2) of this AD, as applicable to airplane
configuration.
(1) For airplanes on which either Saab AB
Modification 2650 or Modification 2859 is
not installed: Modify the stall warning and
identification system, in accordance with the
Accomplishment Instructions of Saab Service
Bulletin 340–27–120, dated July 11, 2014.
(2) For airplanes on which either Saab AB
Modification 2650 or Modification 2859 is
installed, or on which both modifications are
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(j) Parts Installation Prohibitions
After the replacement required by
paragraph (h) of this AD, no person may
install any SWC having P/N 0020AK,
0020AK1, 0020AK2, 0020AK4, 0020AK6,
0020AK7, or 0020AK3 MOD 1, on any
airplane.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Shahram Daneshmandi, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1112; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Saab AB, Saab Aeronautics’ EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0218, dated
September 29, 2014, 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–2015–6544.
(m) 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) Saab Service Bulletin 340–27–109,
dated April 14, 2014.
(ii) Saab Service Bulletin 340–27–116,
dated October 18, 2013.
(iii) Saab Service Bulletin 340–27–120,
dated July 11, 2014.
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76845
(iv) Saab Service Bulletin 340–27–121,
dated July 11, 2014.
(v) Saab Service Bulletin 340–27–122,
dated July 11, 2014.
(3) For service information identified in
this AD, contact Saab AB, Saab Aeronautics,
¨
SE–581 88, Linkoping, Sweden; telephone
+46 13 18 5591; fax +46 13 18 4874; email
saab340.techsupport@saabgroup.com;
Internet https://www.saabgroup.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on October
25, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–26327 Filed 11–3–16; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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.
SUMMARY:
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Federal Register / Vol. 81, No. 214 / Friday, November 4, 2016 / Rules and Regulations
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.
DATES:
You may send comments 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: 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:
https://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 https://
www.regulations.gov by searching for
locating Docket No. FAA–2016–9356.
ADDRESSES:
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–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.
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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:
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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 https://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
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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 https://
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 workhours 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
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Federal Register / Vol. 81, No. 214 / Friday, November 4, 2016 / Rules and Regulations
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.
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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:
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(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.
(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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(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.
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.
§ 39.13
[Amended]
2. The FAA amends § 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.
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(g) Credit for Actions Done Following
Previous Service Information
This AD allows credit for the visual
inspection required in paragraph (f)(1) of this
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Federal Register / Vol. 81, No. 214 / Friday, November 4, 2016 / Rules and Regulations
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
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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 https://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.
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(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: https://www.pilatusaircraft.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 https://
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9306; Directorate
Identifier 2016–NM–169–AD; Amendment
39–18707; AD 2016–22–18]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model MD–90–30
airplanes. This AD requires a detailed
inspection of the forward and aft
surfaces on the left and right sides at the
cant station 1520 bulkhead for any crack
in the upper cap and (cap) doubler,
webs and doublers, stiffeners, and the
lower tee cap between longerons 3
through 11, and repairs if necessary.
This AD was prompted by a report of
cracking in various structures in the
fuselage cant station 1520 bulkhead. We
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
are issuing this AD to detect and correct
cracking in the bulkhead, which could
result in reduced structural integrity of
the airplane.
DATES: This AD is effective November
21, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 21, 2016.
We must receive comments on this
AD by December 19, 2016.
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 final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110–SK57,
Seal Beach, CA 90740–5600; telephone
562–797–1717; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9306.
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–2016–
9306; 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 (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
George Garrido, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
E:\FR\FM\04NOR1.SGM
04NOR1
]]>Agencies
[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.
-----------------------------------------------------------------------
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 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: 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: https://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 https://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 https://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 https://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 https://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 https://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: https://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 https://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: https://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
