Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes, 60243-60246 [2016-20833]
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Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations
model series of airplanes. It is not a rule
of general applicability.
The substance of these special
conditions has been subjected to the
notice and comment period in several
prior instances and has been derived
without substantive change from those
previously issued. It is unlikely that
prior public comment would result in a
significant change from the substance
contained herein. Therefore, the FAA
has determined that prior public notice
and comment are unnecessary, and good
cause exists for adopting these special
conditions upon publication in the
Federal Register. The FAA is requesting
comments to allow interested persons to
submit views that may not have been
submitted in response to the prior
opportunities for comment described
above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued as part of the type certification
basis for Bombardier Model BD–700–
2A12 and BD–700–2A13 airplanes.
1. In addition to meeting the
requirements of § 25.773(b)(1), the
airplane must have a means to maintain
a clear portion of the windshield, during
precipitation conditions, such that both
pilots to have a sufficiently extensive
view along the ground or flight path in
taxi and flight. This means must be
designed to function, without
continuous attention on the part of the
crew, in conditions from light misting
precipitation to heavy rain, at speeds
from fully stopped in still air to 1.5 VSR1
with lift and drag devices retracted, and
in icing conditions specified in
§ 25.1419 if certification for flight in
icing conditions is requested.
2. The precipitation removal system
must comply with § 25.773.
3. Instructions to maintain the
precipitation-removal system must
comply with § 25.1529.
4. The materials used in the
precipitation removal system must
comply with § 25.603.
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[FR Doc. 2016–21079 Filed 8–31–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
33 33; fax: +41 41 619 73 11; email:
SupportPC12@pilatus-aircraft.com;
Internet: www.pilatus-aircraft.com. 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 Docket No. FAA–2016–
7048.
FOR FURTHER INFORMATION CONTACT:
[Docket No. FAA–2016–7048; Directorate
Identifier 2016–CE–014–AD; Amendment
39–18635; AD 2016–18–05]
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.
RIN 2120–AA64
SUPPLEMENTARY INFORMATION:
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; PILATUS
AIRCRAFT LTD. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
PILATUS AIRCRAFT LTD. Models PC–
12, PC–12/45, PC–12/47, and PC–12/
47E airplanes installed with an affected
engine mounting frame assembly. 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 longitudinal material
separation on the internal surface of the
engine mounting frame assembly tubes.
We are issuing this AD to detect and
correct this condition, which could lead
to partial or complete failure of the
structural joint and possibly result in inflight detachment of the engine with
consequent loss of control.
DATES: This AD is effective October 6,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 6, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7048; or in person at Document
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 Support PC–12, CH–6371
Stans, Switzerland; phone: +41 41 619
SUMMARY:
The authority citation for these
special conditions is as follows:
■
■
Issued in Renton, Washington, on August
23, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
60243
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to PILATUS AIRCRAFT LTD.
Models PC–12, PC–12/45, PC–12/47,
and PC–12/47E airplanes installed with
an affected engine mounting frame
assembly. The NPRM was published in
the Federal Register on June 13, 2016
(81 FR 38115). The NPRM proposed to
correct an unsafe condition for the
specified products and was based on
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country.
The MCAI states:
The PC–12 Engine Mounting Frame
Assembly (hereafter referred to as ‘‘EMF’’ in
this AD), Part Number (P/N) 571.20.12.036, is
a welded structure including three special
tubes, P/N 571.20.12.073, P/N 571.20.12.074
and P/N 571.20.12.107, the ends of which are
subject to a special swaging process during
manufacturing. Longitudinal material
separation on the internal surface of the
special tubes was detected on few EMFs on
new production aeroplanes. Investigations
identified the root cause to be an incorrect
accomplishment of the swaging process.
This condition, if not detected and
corrected, could lead to growth of the
material separation and subsequent partial or
complete failure of the structural joint,
possibly resulting in in-flight detachment of
the engine and consequent reduced control,
or loss of control, of the aeroplane.
To address this potential unsafe condition,
Pilatus issued Service Bulletin (SB) No. 71–
009, now at Revision 2 (hereafter referred to
as ‘‘the SB’’ in this AD), to provide
inspection instructions for the affected EMF
to detect indications of material separation.
For the reason described above, this AD
requires identification and inspection of the
affected EMF and, depending on the findings,
their replacement with serviceable EMF.
The MCAI can be found in the AD
docket on the Internet at: https://
www.regulations.gov/
document?D=FAA-2016-7048-0002.
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Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (81
FR 38115, June 13, 2016) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (81 FR
38115, June 13, 2016) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (81 FR 38115,
June 13, 2016).
Related Service Information Under 1
CFR Part 51
We reviewed PILATUS AIRCRAFT
LTD. PILATUS PC–12 Service Bulletin
No: 71–009, Reference No: 345,
Modification No: EC–15–0632, Revision
2, dated March 18, 2016; Pilatus
Powerplant Mounting Frame, Removal/
Installation, Date module/Technical
publication 12–A–71–00–05–00A–
920A–A, dated February 26, 2010,
found in Pilatus Model type–PC–12,
PC–12/45, PC–12/47 MSN–101–888
Aircraft Maintenance Manual (AMM),
Document No. 02049, 12–A–AM–00–
00–00–I; and Pilatus Powerplant
Mounting Frame, Removal/Installation,
Date module/Technical publication 12–
B–71–00–05–00A–920A–A, dated
October 4, 2010, found in Pilatus Model
type–PC–12/47E MSN–1001–UP
Aircraft Maintenance Manual (AMM),
Document No. 02300, 12–B–AM–00–
00–00–I. The service information
describes procedures for determining if
an affected engine mounting frame
assembly (EMF) is installed, inspecting
the EMF, and replacing the EMF with a
serviceable EMF. 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.
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Costs of Compliance
We estimate that this AD will affect
888 products of U.S. registry. We also
estimate that it would take about 3
work-hours per product to comply with
the basic 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 $226,440, or $255 per product.
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In addition, we estimate that any
necessary follow-on actions would cost
the following amounts. We have no way
of determining the number of products
that may need these actions.
The visual and eddy current
inspections would take about 3 workhours for a cost of $255 per product.
The replacement of the EMF would
take about 90 work-hours and require
parts costing $33,336, for a cost of
$40,986 per product.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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
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under the criteria of the Regulatory
Flexibility Act.
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–
7048; 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2016–18–05 PILATUS AIRCRAFT LTD.:
Amendment 39–18635; Docket No.
FAA–2016–7048; Directorate Identifier
2016–CE–014–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective October 6, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to PILATUS AIRCRAFT
LTD. Models PC–12, PC–12/45, PC–12/47,
and PC–12/47E airplanes, all serial numbers,
that are:
(1) Installed with an affected serial number
engine mounting frame assembly (EMF), part
number (P/N) 571.20.12.036, listed in figure
1 of paragraph (c)(1) of this AD; and
FIGURE 1 TO PARAGRAPH (c)(1) OF
THIS AD: EMF P/N 571.20.12.036,
AFFECTED SERIAL NUMBERS
0001
1202
1275
1325
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through
through
through
through
1200
1272
1323
1328
01SER1
inclusive.
inclusive.
inclusive.
inclusive.
Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations
FIGURE 1 TO PARAGRAPH (c)(1) OF
THIS AD: EMF P/N 571.20.12.036,
AFFECTED SERIAL NUMBERS—Continued
1334 through 1338 inclusive.
1340 and 1342.
1344 through 1346 inclusive.
1348 and 1349.
1358, 1361, and 1365.
(2) Certificated in any category.
(d) Subject
Air Transport Association of America
(ATA) Code 71: Power Plant.
(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
longitudinal material separation on the
internal surface of the engine mounting frame
assembly tubes (EMF). We are issuing this
AD to detect and correct material separation
on the internal surface of the engine
mounting frame assembly tubes, which could
lead to partial or complete failure of the
structural joint and possibly result in inflight detachment of the engine with
consequent loss of control.
(f) Actions and Compliance
Do the actions in paragraphs (f)(1) through
(7) of this AD. If paragraphs (f)(1) through (6)
of this AD have already been done before
October 6, 2016 (the effective date of this
AD), then only paragraph (f)(7) of this AD
applies.
(1) Within the compliance time identified
in figure 2 of paragraph (f)(1) of this AD, do
an ultrasonic inspection of the swaged engine
mounting tube ends of the affected EMF
following the instructions of paragraph
3.B.(1) of PILATUS AIRCRAFT LTD
PILATUS PC–12 Service Bulletin No: 71–
009, Reference No: 345, Modification No:
EC–15–0632, Revision 2, dated March 18,
2016.
FIGURE 2 TO PARAGRAPH (f)(1) OF
THIS AD: INITIAL COMPLIANCE TIME
A or B, Whichever Occurs Later
A ...........
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B ...........
Before the EMF exceeds 11,000
hours time-in-service (TIS) or
13,500 flight cycles (FC), whichever occurs first since first installation of the EMF on an airplane.
Within 1,000 hours TIS or 1,000
FC or 6 months, whichever occurs first after October 6, 2016
(the effective date of this AD).
(2) If an indication with an echo of less
than 40 percent full screen height is detected
on an EMF during the ultrasonic inspection
required in paragraph (f)(1) of this AD, except
for paragraph (f)(7), no further actions are
required for this AD. Document compliance
with this AD in the maintenance records.
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(3) If an indication with an echo of 40
percent full screen height or more is detected
on an EMF during the ultrasonic inspection
required in paragraph (f)(1) of this AD, do the
actions in paragraphs (f)(3)(i) through (iii) of
this AD, as applicable.
(i) Before further flight and repetitively
thereafter at intervals not to exceed 600 hours
TIS or 12 months, whichever occurs first, do
a visual inspection of the welding and do an
eddy current inspection of the tubes at the
indication point detected during the
ultrasonic inspection. Use the instructions of
paragraphs 3.B.(2) and 3.B.(3) of PILATUS
AIRCRAFT LTD PILATUS PC–12 Service
Bulletin No: 71–009, Reference No: 345,
Modification No: EC–15–0632, Revision 2,
dated March 18, 2016.
(ii) If any cracks are found during any of
the visual inspections or if an indication with
a signal of 20 percent or more is detected
during any of the eddy current inspections
required in paragraph (f)(3)(i) of this AD,
before further flight, replace the EMF with a
serviceable EMF following the instructions in
the service information listed in paragraph
(f)(5) of this AD, including all subparagraphs
as applicable.
(iii) Unless already done as required by
paragraph (f)(3)(ii) of this AD, with≤in 1,800
hours TIS or 36 months after the initial visual
and eddy current inspections of the affected
EMF required by paragraph (f)(3)(i) of this
AD, whichever occurs first, replace the EMF
with a serviceable EMF following the
instructions in the service information listed
in paragraph (f)(5) of this AD, including all
subparagraphs as applicable.
(4) For the purpose of this AD, a
serviceable EMF is defined as any EMF that
is not listed in figure 1 of paragraph (c)(1) of
this AD or an affected EMF that is listed in
figure 1 of paragraph (c)(1) of this AD but has
had the ultrasonic inspection required in
paragraph (f)(1) of this AD and had an
indication with an echo of less than 40
percent full screen height.
(5) For replacement of the EMF, follow the
instructions listed in paragraphs (f)(5)(i) and
(ii), as applicable.
(i) For Models PC–12, PC–12/45, and PC–
12/47, manufacturer serial numbers (MSN)
101–888: Pilatus Powerplant Mounting
Frame, Removal/Installation, Date module/
Technical publication 12–A–71–00–05–00A–
920A–A, dated February 26, 2010, found in
Pilatus Model type-PC–12, PC–12/45, PC–12/
47 MSN–101–888 Aircraft Maintenance
Manual (AMM), Document No. 02049, 12–A–
AM–00–00–00–I.
(ii) For Model PC–12/47E, MSN 1001 and
up: Pilatus Powerplant Mounting Frame,
Removal/Installation, Date module/Technical
publication 12–B–71–00–05–00A–920A–A,
dated October 4, 2010, found in Pilatus
Model type-PC–12/47E MSN–1001–UP
Aircraft Maintenance Manual (AMM),
Document No. 02300, 12–B–AM–00–00–00–
I.
(6) If an EMF has an indication with an
echo of 40 percent or more during the
ultrasonic inspection required in paragraph
(f)(1) of this AD, you may replace the EMF
with a serviceable EMF in lieu of the visual
or eddy current inspections required in
paragraph (f)(3)(i) of this AD. For
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60245
replacement of the EMF, follow the
instructions in the service information listed
in paragraph (f)(5) of this AD, including all
subparagraphs as applicable.
(7) As of October 6, 2016 (the effective date
of this AD), do not install an EMF P/N
571.20.12.036 unless it has been determined
to be a serviceable EMF as specified in
paragraph (f)(4) of this AD.
(8) Airplanes with an MSN of 1556 or
higher are not affected by this AD provided
that the EMF has not been replaced since its
manufacture. A review of the maintenance
records, Airworthiness Approval Tag (FAA
Form 8130–3), or other positive form of parts
identification such as a shipping ticket,
invoice, or direct ship authority letter, can be
used to determine the serial number of the
EMF.
(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 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.
(h) Related Information
(1) Refer to MCAI European Aviation
Safety Agency (EASA) AD No. 2016–0081,
dated April 25, 2016, for related information
pertaining to this AD. The MCAI can be
found in the AD docket on the Internet at:
https://www.regulations.gov/
document?D=FAA-2016-7048-0002.
(i) 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) PILATUS PC–12 Service Bulletin No:
71–009, Reference No: 345, Modification No:
EC–15–0632, Revision 2, dated March 18,
2016;
(ii) Pilatus Powerplant Mounting Frame,
Removal/Installation, Date module/Technical
publication 12–A–71–00–05–00A–920A–A,
dated February 26, 2010, found in Pilatus
Model type-PC–12, PC–12/45, PC–12/47
MSN–101–888 Aircraft Maintenance Manual
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01SER1
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(AMM), Document No. 02049, 12–A–AM–
00–00–00–I; and
(iii) Pilatus Powerplant Mounting Frame,
Removal/Installation, Date module/Technical
publication 12–B–71–00–05–00A–920A–A,
dated October 4, 2010, found in Pilatus
Model type- PC–12/47E MSN–1001–UP
Aircraft Maintenance Manual (AMM),
Document No. 02300, 12–B–AM–00–00–00–
I.
(3) For service information identified in
this AD, contact Pilatus Aircraft Ltd.,
Customer Support PC–12, CH–6371 Stans,
Switzerland; phone: +41 41 619 33 33; fax:
+41 41 619 73 11; email:
SupportPC12@pilatus-aircraft.com; Internet:
www.pilatus-aircraft.com.
(4) You may view this 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. In
addition, you can access this service
information on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2016–7048.
(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 August
23, 2016.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–20833 Filed 8–31–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5460; Directorate
Identifier 2015–NM–188–AD; Amendment
39–18599; AD 2016–16–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to certain Airbus Model
A330–200 Freighter, –200, and –300
series airplanes. Paragraphs (i) and (l) of
the regulatory text contain
typographical errors in the service
bulletin number. This document
corrects those errors. In all other
respects, the original document remains
the same.
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SUMMARY:
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This final rule is effective
September 8, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 8, 2016 (81 FR 51325,
August 4, 2016).
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office–EAL,
1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5
61 93 36 96; fax: +33 5 61 93 45 80;
email: airworthiness.A330-A340@
airbus.com; Internet: https://
www.airbus.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–2016–5460.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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 address for the
Docket Office (phone: 800–647–5527) is
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 FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone: 425–227–1138;
fax: 425–227–1149.
SUPPLEMENTARY INFORMATION:
Airworthiness Directive 2016–16–01,
Amendment 39–18599 (81 FR 51325,
August 4, 2016) (‘‘AD 2016–16–01’’),
currently requires an inspection of
affected structural parts in the cargo and
cabin compartments to determine if
proper heat treatment has been done,
and replacement if necessary, for certain
Airbus Model A330–200 Freighter,
–200, and –300 series airplanes.
Need for the Correction
As published, paragraphs (i) and (l) of
the regulatory text identify the service
information by the wrong service
bulletin number. Where paragraphs (i)
and (l) incorrectly specify Airbus
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
Service Bulletins ‘‘A320–53–3227’’ and
‘‘A320–53–3228,’’ the correct service
bulletin numbers are ‘‘A330–53–3227’’
and ‘‘A330–53–3228,’’ respectively.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Airbus Service Bulletin A330–53–
3227, dated August 18, 2015. The
service information describes
procedures to inspect affected structural
parts in the cargo compartment to
determine if proper heat treatment has
been done, and replacement of parts;
and
• Airbus Service Bulletin A330–53–
3228, dated August 18, 2015. The
service information describes
procedures to inspect affected structural
parts in the cabin compartment to
determine if proper heat treatment has
been done, and replacement of 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.
Correction of Publication
This document corrects two errors
and correctly adds the AD as an
amendment to 14 CFR 39.13. Although
no other part of the preamble or
regulatory information has been
corrected, we are publishing the entire
rule in the Federal Register.
The effective date of this AD remains
September 8, 2016.
Since this action only corrects a
typographical error in two locations, it
has no adverse economic impact and
imposes no additional burden on any
person. Therefore, we have determined
that notice and public procedures are
unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Correction
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration amends part 39 of the
Federal Aviation Regulations (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.
E:\FR\FM\01SER1.SGM
01SER1
]]>Agencies
[Federal Register Volume 81, Number 170 (Thursday, September 1, 2016)]
[Rules and Regulations]
[Pages 60243-60246]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20833]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7048; Directorate Identifier 2016-CE-014-AD;
Amendment 39-18635; AD 2016-18-05]
RIN 2120-AA64
Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for PILATUS
AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes
installed with an affected engine mounting frame assembly. 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 longitudinal material separation on the
internal surface of the engine mounting frame assembly tubes. We are
issuing this AD to detect and correct this condition, which could lead
to partial or complete failure of the structural joint and possibly
result in in-flight detachment of the engine with consequent loss of
control.
DATES: This AD is effective October 6, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 6,
2016.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7048; or in person at Document 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 Support PC-12, CH-6371 Stans, Switzerland;
phone: +41 41 619 33 33; fax: +41 41 619 73 11; email:
aircraft.com">SupportPC12@pilatus-aircraft.com; Internet: www.pilatus-aircraft.com.
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 Docket No. FAA-2016-7048.
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 by adding an AD that would apply to PILATUS AIRCRAFT LTD.
Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes installed
with an affected engine mounting frame assembly. The NPRM was published
in the Federal Register on June 13, 2016 (81 FR 38115). The NPRM
proposed to correct an unsafe condition for the specified products and
was based on mandatory continuing airworthiness information (MCAI)
originated by an aviation authority of another country. The MCAI
states:
The PC-12 Engine Mounting Frame Assembly (hereafter referred to
as ``EMF'' in this AD), Part Number (P/N) 571.20.12.036, is a welded
structure including three special tubes, P/N 571.20.12.073, P/N
571.20.12.074 and P/N 571.20.12.107, the ends of which are subject
to a special swaging process during manufacturing. Longitudinal
material separation on the internal surface of the special tubes was
detected on few EMFs on new production aeroplanes. Investigations
identified the root cause to be an incorrect accomplishment of the
swaging process.
This condition, if not detected and corrected, could lead to
growth of the material separation and subsequent partial or complete
failure of the structural joint, possibly resulting in in-flight
detachment of the engine and consequent reduced control, or loss of
control, of the aeroplane.
To address this potential unsafe condition, Pilatus issued
Service Bulletin (SB) No. 71-009, now at Revision 2 (hereafter
referred to as ``the SB'' in this AD), to provide inspection
instructions for the affected EMF to detect indications of material
separation.
For the reason described above, this AD requires identification
and inspection of the affected EMF and, depending on the findings,
their replacement with serviceable EMF.
The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/document?D=FAA-2016-7048-0002.
[[Page 60244]]
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (81 FR 38115, June 13,
2016) or on the determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (81 FR 38115, June 13, 2016) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (81 FR 38115, June 13, 2016).
Related Service Information Under 1 CFR Part 51
We reviewed PILATUS AIRCRAFT LTD. PILATUS PC-12 Service Bulletin
No: 71-009, Reference No: 345, Modification No: EC-15-0632, Revision 2,
dated March 18, 2016; Pilatus Powerplant Mounting Frame, Removal/
Installation, Date module/Technical publication 12-A-71-00-05-00A-920A-
A, dated February 26, 2010, found in Pilatus Model type-PC-12, PC-12/
45, PC-12/47 MSN-101-888 Aircraft Maintenance Manual (AMM), Document
No. 02049, 12-A-AM-00-00-00-I; and Pilatus Powerplant Mounting Frame,
Removal/Installation, Date module/Technical publication 12-B-71-00-05-
00A-920A-A, dated October 4, 2010, found in Pilatus Model type-PC-12/
47E MSN-1001-UP Aircraft Maintenance Manual (AMM), Document No. 02300,
12-B-AM-00-00-00-I. The service information describes procedures for
determining if an affected engine mounting frame assembly (EMF) is
installed, inspecting the EMF, and replacing the EMF with a serviceable
EMF. 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.
Costs of Compliance
We estimate that this AD will affect 888 products of U.S. registry.
We also estimate that it would take about 3 work-hours per product to
comply with the basic 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 $226,440, or $255 per product.
In addition, we estimate that any necessary follow-on actions would
cost the following amounts. We have no way of determining the number of
products that may need these actions.
The visual and eddy current inspections would take about 3 work-
hours for a cost of $255 per product.
The replacement of the EMF would take about 90 work-hours and
require parts costing $33,336, for a cost of $40,986 per product.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7048; 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
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:
2016-18-05 PILATUS AIRCRAFT LTD.: Amendment 39-18635; Docket No.
FAA-2016-7048; Directorate Identifier 2016-CE-014-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective October 6,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45,
PC-12/47, and PC-12/47E airplanes, all serial numbers, that are:
(1) Installed with an affected serial number engine mounting
frame assembly (EMF), part number (P/N) 571.20.12.036, listed in
figure 1 of paragraph (c)(1) of this AD; and
Figure 1 to Paragraph (c)(1) of this AD: EMF P/N 571.20.12.036, Affected
Serial Numbers
------------------------------------------------------------------------
-------------------------------------------------------------------------
0001 through 1200 inclusive.
1202 through 1272 inclusive.
1275 through 1323 inclusive.
1325 through 1328 inclusive.
[[Page 60245]]
1334 through 1338 inclusive.
1340 and 1342.
1344 through 1346 inclusive.
1348 and 1349.
1358, 1361, and 1365.
------------------------------------------------------------------------
(2) Certificated in any category.
(d) Subject
Air Transport Association of America (ATA) Code 71: Power Plant.
(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 longitudinal
material separation on the internal surface of the engine mounting
frame assembly tubes (EMF). We are issuing this AD to detect and
correct material separation on the internal surface of the engine
mounting frame assembly tubes, which could lead to partial or
complete failure of the structural joint and possibly result in in-
flight detachment of the engine with consequent loss of control.
(f) Actions and Compliance
Do the actions in paragraphs (f)(1) through (7) of this AD. If
paragraphs (f)(1) through (6) of this AD have already been done
before October 6, 2016 (the effective date of this AD), then only
paragraph (f)(7) of this AD applies.
(1) Within the compliance time identified in figure 2 of
paragraph (f)(1) of this AD, do an ultrasonic inspection of the
swaged engine mounting tube ends of the affected EMF following the
instructions of paragraph 3.B.(1) of PILATUS AIRCRAFT LTD PILATUS
PC-12 Service Bulletin No: 71-009, Reference No: 345, Modification
No: EC-15-0632, Revision 2, dated March 18, 2016.
Figure 2 to Paragraph (f)(1) of This AD: Initial Compliance Time
------------------------------------------------------------------------
------------------------------------------------------------------------
A or B, Whichever Occurs Later
------------------------------------------------------------------------
A...................................... Before the EMF exceeds 11,000
hours time-in-service (TIS) or
13,500 flight cycles (FC),
whichever occurs first since
first installation of the EMF
on an airplane.
B...................................... Within 1,000 hours TIS or 1,000
FC or 6 months, whichever
occurs first after October 6,
2016 (the effective date of
this AD).
------------------------------------------------------------------------
(2) If an indication with an echo of less than 40 percent full
screen height is detected on an EMF during the ultrasonic inspection
required in paragraph (f)(1) of this AD, except for paragraph
(f)(7), no further actions are required for this AD. Document
compliance with this AD in the maintenance records.
(3) If an indication with an echo of 40 percent full screen
height or more is detected on an EMF during the ultrasonic
inspection required in paragraph (f)(1) of this AD, do the actions
in paragraphs (f)(3)(i) through (iii) of this AD, as applicable.
(i) Before further flight and repetitively thereafter at
intervals not to exceed 600 hours TIS or 12 months, whichever occurs
first, do a visual inspection of the welding and do an eddy current
inspection of the tubes at the indication point detected during the
ultrasonic inspection. Use the instructions of paragraphs 3.B.(2)
and 3.B.(3) of PILATUS AIRCRAFT LTD PILATUS PC-12 Service Bulletin
No: 71-009, Reference No: 345, Modification No: EC-15-0632, Revision
2, dated March 18, 2016.
(ii) If any cracks are found during any of the visual
inspections or if an indication with a signal of 20 percent or more
is detected during any of the eddy current inspections required in
paragraph (f)(3)(i) of this AD, before further flight, replace the
EMF with a serviceable EMF following the instructions in the service
information listed in paragraph (f)(5) of this AD, including all
subparagraphs as applicable.
(iii) Unless already done as required by paragraph (f)(3)(ii) of
this AD, with>in 1,800 hours TIS or 36 months after the initial
visual and eddy current inspections of the affected EMF required by
paragraph (f)(3)(i) of this AD, whichever occurs first, replace the
EMF with a serviceable EMF following the instructions in the service
information listed in paragraph (f)(5) of this AD, including all
subparagraphs as applicable.
(4) For the purpose of this AD, a serviceable EMF is defined as
any EMF that is not listed in figure 1 of paragraph (c)(1) of this
AD or an affected EMF that is listed in figure 1 of paragraph (c)(1)
of this AD but has had the ultrasonic inspection required in
paragraph (f)(1) of this AD and had an indication with an echo of
less than 40 percent full screen height.
(5) For replacement of the EMF, follow the instructions listed
in paragraphs (f)(5)(i) and (ii), as applicable.
(i) For Models PC-12, PC-12/45, and PC-12/47, manufacturer
serial numbers (MSN) 101-888: Pilatus Powerplant Mounting Frame,
Removal/Installation, Date module/Technical publication 12-A-71-00-
05-00A-920A-A, dated February 26, 2010, found in Pilatus Model type-
PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft Maintenance Manual
(AMM), Document No. 02049, 12-A-AM-00-00-00-I.
(ii) For Model PC-12/47E, MSN 1001 and up: Pilatus Powerplant
Mounting Frame, Removal/Installation, Date module/Technical
publication 12-B-71-00-05-00A-920A-A, dated October 4, 2010, found
in Pilatus Model type-PC-12/47E MSN-1001-UP Aircraft Maintenance
Manual (AMM), Document No. 02300, 12-B-AM-00-00-00-I.
(6) If an EMF has an indication with an echo of 40 percent or
more during the ultrasonic inspection required in paragraph (f)(1)
of this AD, you may replace the EMF with a serviceable EMF in lieu
of the visual or eddy current inspections required in paragraph
(f)(3)(i) of this AD. For replacement of the EMF, follow the
instructions in the service information listed in paragraph (f)(5)
of this AD, including all subparagraphs as applicable.
(7) As of October 6, 2016 (the effective date of this AD), do
not install an EMF P/N 571.20.12.036 unless it has been determined
to be a serviceable EMF as specified in paragraph (f)(4) of this AD.
(8) Airplanes with an MSN of 1556 or higher are not affected by
this AD provided that the EMF has not been replaced since its
manufacture. A review of the maintenance records, Airworthiness
Approval Tag (FAA Form 8130-3), or other positive form of parts
identification such as a shipping ticket, invoice, or direct ship
authority letter, can be used to determine the serial number of the
EMF.
(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 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.
(h) Related Information
(1) Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2016-0081, dated April 25, 2016, for related information pertaining
to this AD. The MCAI can be found in the AD docket on the Internet
at: https://www.regulations.gov/document?D=FAA-2016-7048-0002.
(i) 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) PILATUS PC-12 Service Bulletin No: 71-009, Reference No:
345, Modification No: EC-15-0632, Revision 2, dated March 18, 2016;
(ii) Pilatus Powerplant Mounting Frame, Removal/Installation,
Date module/Technical publication 12-A-71-00-05-00A-920A-A, dated
February 26, 2010, found in Pilatus Model type-PC-12, PC-12/45, PC-
12/47 MSN-101-888 Aircraft Maintenance Manual
[[Page 60246]]
(AMM), Document No. 02049, 12-A-AM-00-00-00-I; and
(iii) Pilatus Powerplant Mounting Frame, Removal/Installation,
Date module/Technical publication 12-B-71-00-05-00A-920A-A, dated
October 4, 2010, found in Pilatus Model type- PC-12/47E MSN-1001-UP
Aircraft Maintenance Manual (AMM), Document No. 02300, 12-B-AM-00-
00-00-I.
(3) For service information identified in this AD, contact
Pilatus Aircraft Ltd., Customer Support PC-12, CH-6371 Stans,
Switzerland; phone: +41 41 619 33 33; fax: +41 41 619 73 11; email:
aircraft.com">SupportPC12@pilatus-aircraft.com; Internet: www.pilatus-
aircraft.com.
(4) You may view this 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. In addition, you can access this service information
on the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2016-7048.
(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 August 23, 2016.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-20833 Filed 8-31-16; 8:45 am]
BILLING CODE 4910-13-P
