81 FR 60243 - Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 170 (September 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 170 (September 1, 2016)
| Page Range | 60243-60246 | |
| FR Document | 2016-20833 |
[Federal Register Volume 81, Number 170 (Thursday, September 1, 2016)] [Rules and Regulations] [Pages 60243-60246] From the Federal Register Online [www.thefederalregister.org] [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 http://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">[email protected]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 http://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: [email protected]. 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 http://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: [email protected]. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (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">[email protected]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 http://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: http://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
![Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 60243
model series of airplanes. It is not a rule Issued in Renton, Washington, on August 33 33; fax: +41 41 619 73 11; email:
of general applicability. 23, 2016. SupportPC12@pilatus-aircraft.com;
John P. Piccola, Jr., Internet: www.pilatus-aircraft.com. For
The substance of these special
conditions has been subjected to the Acting Manager, Transport Airplane information on the availability of this
Directorate, Aircraft Certification Service. material at the FAA, call (816) 329–
notice and comment period in several
[FR Doc. 2016–21079 Filed 8–31–16; 8:45 am] 4148. It is also available on the Internet
prior instances and has been derived
BILLING CODE 4910–13–P at http://www.regulations.gov by
without substantive change from those
searching for Docket No. FAA–2016–
previously issued. It is unlikely that 7048.
prior public comment would result in a DEPARTMENT OF TRANSPORTATION
significant change from the substance FOR FURTHER INFORMATION CONTACT:
contained herein. Therefore, the FAA Federal Aviation Administration Doug Rudolph, Aerospace Engineer,
has determined that prior public notice FAA, Small Airplane Directorate, 901
and comment are unnecessary, and good 14 CFR Part 39 Locust, Room 301, Kansas City,
cause exists for adopting these special Missouri 64106; telephone: (816) 329–
[Docket No. FAA–2016–7048; Directorate 4059; fax: (816) 329–4090; email:
conditions upon publication in the Identifier 2016–CE–014–AD; Amendment
Federal Register. The FAA is requesting 39–18635; AD 2016–18–05]
doug.rudolph@faa.gov.
comments to allow interested persons to SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
submit views that may not have been
submitted in response to the prior Discussion
Airworthiness Directives; PILATUS
opportunities for comment described AIRCRAFT LTD. Airplanes We issued a notice of proposed
above. rulemaking (NPRM) to amend 14 CFR
AGENCY: Federal Aviation part 39 by adding an AD that would
List of Subjects in 14 CFR Part 25 Administration (FAA), Department of apply to PILATUS AIRCRAFT LTD.
Transportation (DOT). Models PC–12, PC–12/45, PC–12/47,
Aircraft, Aviation safety, Reporting
and recordkeeping requirements. ACTION: Final rule. and PC–12/47E airplanes installed with
an affected engine mounting frame
■ The authority citation for these SUMMARY: We are adopting a new assembly. The NPRM was published in
special conditions is as follows: airworthiness directive (AD) for the Federal Register on June 13, 2016
PILATUS AIRCRAFT LTD. Models PC– (81 FR 38115). The NPRM proposed to
Authority: 49 U.S.C. 106(g), 40113, 44701, 12, PC–12/45, PC–12/47, and PC–12/
44702, 44704. correct an unsafe condition for the
47E airplanes installed with an affected specified products and was based on
The Special Conditions engine mounting frame assembly. This mandatory continuing airworthiness
AD results from mandatory continuing information (MCAI) originated by an
■ Accordingly, pursuant to the authority airworthiness information (MCAI) aviation authority of another country.
delegated to me by the Administrator, issued by an aviation authority of The MCAI states:
the following special conditions are another country to identify and correct
an unsafe condition on an aviation The PC–12 Engine Mounting Frame
issued as part of the type certification
product. The MCAI describes the unsafe Assembly (hereafter referred to as ‘‘EMF’’ in
basis for Bombardier Model BD–700– this AD), Part Number (P/N) 571.20.12.036, is
2A12 and BD–700–2A13 airplanes. condition as longitudinal material a welded structure including three special
separation on the internal surface of the tubes, P/N 571.20.12.073, P/N 571.20.12.074
1. In addition to meeting the engine mounting frame assembly tubes.
requirements of § 25.773(b)(1), the and P/N 571.20.12.107, the ends of which are
We are issuing this AD to detect and subject to a special swaging process during
airplane must have a means to maintain correct this condition, which could lead manufacturing. Longitudinal material
a clear portion of the windshield, during to partial or complete failure of the separation on the internal surface of the
precipitation conditions, such that both structural joint and possibly result in in- special tubes was detected on few EMFs on
pilots to have a sufficiently extensive flight detachment of the engine with new production aeroplanes. Investigations
view along the ground or flight path in consequent loss of control. identified the root cause to be an incorrect
taxi and flight. This means must be accomplishment of the swaging process.
DATES: This AD is effective October 6, This condition, if not detected and
designed to function, without 2016. corrected, could lead to growth of the
continuous attention on the part of the The Director of the Federal Register material separation and subsequent partial or
crew, in conditions from light misting approved the incorporation by reference complete failure of the structural joint,
precipitation to heavy rain, at speeds of certain publications listed in the AD possibly resulting in in-flight detachment of
from fully stopped in still air to 1.5 VSR1 as of October 6, 2016. the engine and consequent reduced control,
with lift and drag devices retracted, and or loss of control, of the aeroplane.
ADDRESSES: You may examine the AD To address this potential unsafe condition,
in icing conditions specified in docket on the Internet at http:// Pilatus issued Service Bulletin (SB) No. 71–
§ 25.1419 if certification for flight in www.regulations.gov by searching for 009, now at Revision 2 (hereafter referred to
icing conditions is requested. and locating Docket No. FAA–2016– as ‘‘the SB’’ in this AD), to provide
2. The precipitation removal system 7048; or in person at Document inspection instructions for the affected EMF
must comply with § 25.773. Management Facility, U.S. Department to detect indications of material separation.
asabaliauskas on DSK3SPTVN1PROD with RULES
of Transportation, Docket Operations, For the reason described above, this AD
3. Instructions to maintain the requires identification and inspection of the
M–30, West Building Ground Floor,
precipitation-removal system must affected EMF and, depending on the findings,
Room W12–140, 1200 New Jersey their replacement with serviceable EMF.
comply with § 25.1529. Avenue SE., Washington, DC 20590.
4. The materials used in the For service information identified in The MCAI can be found in the AD
precipitation removal system must this AD, contact Pilatus Aircraft Ltd., docket on the Internet at: https://
comply with § 25.603. Customer Support PC–12, CH–6371 www.regulations.gov/
Stans, Switzerland; phone: +41 41 619 document?D=FAA-2016-7048-0002.
VerDate Sep<11>2014 16:43 Aug 31, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\01SER1.SGM 01SER1](https://thefederalregister.org/doc/81_FR_60413/page/1.svg)
![60244 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations
Comments In addition, we estimate that any under the criteria of the Regulatory
We gave the public the opportunity to necessary follow-on actions would cost Flexibility Act.
participate in developing this AD. We the following amounts. We have no way
Examining the AD Docket
received no comments on the NPRM (81 of determining the number of products
that may need these actions. You may examine the AD docket on
FR 38115, June 13, 2016) or on the the Internet at http://
The visual and eddy current
determination of the cost to the public. www.regulations.gov by searching for
inspections would take about 3 work-
Conclusion hours for a cost of $255 per product. and locating Docket No. FAA–2016–
The replacement of the EMF would 7048; or in person at the Docket
We reviewed the relevant data and
take about 90 work-hours and require Management Facility between 9 a.m.
determined that air safety and the
parts costing $33,336, for a cost of and 5 p.m., Monday through Friday,
public interest require adopting the AD
$40,986 per product. except Federal holidays. The AD docket
as proposed except for minor editorial
According to the manufacturer, some contains the NPRM, the regulatory
changes. We have determined that these
of the costs of this AD may be covered evaluation, any comments received, and
minor changes:
under warranty, thereby reducing the other information. The street address for
• Are consistent with the intent that
cost impact on affected individuals. We the Docket Office (telephone (800) 647–
was proposed in the NPRM (81 FR
do not control warranty coverage for 5527) is in the ADDRESSES section.
38115, June 13, 2016) for correcting the
affected individuals. As a result, we Comments will be available in the AD
unsafe condition; and
have included all costs in our cost docket shortly after receipt.
• Do not add any additional burden estimate.
upon the public than was already List of Subjects in 14 CFR Part 39
proposed in the NPRM (81 FR 38115, Authority for This Rulemaking Air transportation, Aircraft, Aviation
June 13, 2016). Title 49 of the United States Code safety, Incorporation by reference,
Related Service Information Under 1 specifies the FAA’s authority to issue Safety.
CFR Part 51 rules on aviation safety. Subtitle I,
Adoption of the Amendment
section 106, describes the authority of
We reviewed PILATUS AIRCRAFT the FAA Administrator. ‘‘Subtitle VII: Accordingly, under the authority
LTD. PILATUS PC–12 Service Bulletin Aviation Programs,’’ describes in more delegated to me by the Administrator,
No: 71–009, Reference No: 345, detail the scope of the Agency’s the FAA amends 14 CFR part 39 as
Modification No: EC–15–0632, Revision authority. follows:
2, dated March 18, 2016; Pilatus We are issuing this rulemaking under
Powerplant Mounting Frame, Removal/ the authority described in ‘‘Subtitle VII, PART 39—AIRWORTHINESS
Installation, Date module/Technical Part A, Subpart III, Section 44701: DIRECTIVES
publication 12–A–71–00–05–00A– General requirements.’’ Under that
920A–A, dated February 26, 2010, ■ 1. The authority citation for part 39
section, Congress charges the FAA with continues to read as follows:
found in Pilatus Model type–PC–12, promoting safe flight of civil aircraft in
PC–12/45, PC–12/47 MSN–101–888 air commerce by prescribing regulations Authority: 49 U.S.C. 106(g), 40113, 44701.
Aircraft Maintenance Manual (AMM), for practices, methods, and procedures
Document No. 02049, 12–A–AM–00– § 39.13 [Amended]
the Administrator finds necessary for
00–00–I; and Pilatus Powerplant safety in air commerce. This regulation ■ 2. The FAA amends § 39.13 by adding
Mounting Frame, Removal/Installation, is within the scope of that authority the following new AD:
Date module/Technical publication 12– because it addresses an unsafe condition 2016–18–05 PILATUS AIRCRAFT LTD.:
B–71–00–05–00A–920A–A, dated that is likely to exist or develop on Amendment 39–18635; Docket No.
October 4, 2010, found in Pilatus Model products identified in this rulemaking FAA–2016–7048; Directorate Identifier
type–PC–12/47E MSN–1001–UP action. 2016–CE–014–AD.
Aircraft Maintenance Manual (AMM), (a) Effective Date
Document No. 02300, 12–B–AM–00– Regulatory Findings
00–00–I. The service information This airworthiness directive (AD) becomes
We determined that this AD will not effective October 6, 2016.
describes procedures for determining if have federalism implications under
an affected engine mounting frame Executive Order 13132. This AD will (b) Affected ADs
assembly (EMF) is installed, inspecting not have a substantial direct effect on None.
the EMF, and replacing the EMF with a the States, on the relationship between (c) Applicability
serviceable EMF. This service the national government and the States,
information is reasonably available This AD applies to PILATUS AIRCRAFT
or on the distribution of power and LTD. Models PC–12, PC–12/45, PC–12/47,
because the interested parties have responsibilities among the various and PC–12/47E airplanes, all serial numbers,
access to it through their normal course levels of government. that are:
of business or by the means identified For the reasons discussed above, I (1) Installed with an affected serial number
in the ADDRESSES section of this AD. certify this AD: engine mounting frame assembly (EMF), part
Costs of Compliance (1) Is not a ‘‘significant regulatory number (P/N) 571.20.12.036, listed in figure
action’’ under Executive Order 12866, 1 of paragraph (c)(1) of this AD; and
We estimate that this AD will affect (2) Is not a ‘‘significant rule’’ under
asabaliauskas on DSK3SPTVN1PROD with RULES
888 products of U.S. registry. We also the DOT Regulatory Policies and FIGURE 1 TO PARAGRAPH (c)(1) OF
estimate that it would take about 3 Procedures (44 FR 11034, February 26, THIS AD: EMF P/N 571.20.12.036,
work-hours per product to comply with 1979), AFFECTED SERIAL NUMBERS
the basic requirements of this AD. The (3) Will not affect intrastate aviation
average labor rate is $85 per work-hour. in Alaska, and 0001 through 1200 inclusive.
Based on these figures, we estimate (4) Will not have a significant 1202 through 1272 inclusive.
the cost of this AD on U.S. operators to economic impact, positive or negative, 1275 through 1323 inclusive.
be $226,440, or $255 per product. on a substantial number of small entities 1325 through 1328 inclusive.
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![60246 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations
(AMM), Document No. 02049, 12–A–AM– DATES: This final rule is effective Service Bulletins ‘‘A320–53–3227’’ and
00–00–00–I; and September 8, 2016. ‘‘A320–53–3228,’’ the correct service
(iii) Pilatus Powerplant Mounting Frame, The Director of the Federal Register bulletin numbers are ‘‘A330–53–3227’’
Removal/Installation, Date module/Technical approved the incorporation by reference and ‘‘A330–53–3228,’’ respectively.
publication 12–B–71–00–05–00A–920A–A,
dated October 4, 2010, found in Pilatus of certain publications listed in this AD
Related Service Information Under 1
Model type- PC–12/47E MSN–1001–UP as of September 8, 2016 (81 FR 51325,
CFR Part 51
Aircraft Maintenance Manual (AMM), August 4, 2016).
Document No. 02300, 12–B–AM–00–00–00– ADDRESSES: For service information Airbus has issued the following
I. identified in this final rule, contact service information:
(3) For service information identified in
this AD, contact Pilatus Aircraft Ltd.,
Airbus SAS, Airworthiness Office–EAL, • Airbus Service Bulletin A330–53–
1 Rond Point Maurice Bellonte, 31707 3227, dated August 18, 2015. The
Customer Support PC–12, CH–6371 Stans,
Switzerland; phone: +41 41 619 33 33; fax: Blagnac Cedex, France; telephone: +33 5 service information describes
+41 41 619 73 11; email: 61 93 36 96; fax: +33 5 61 93 45 80; procedures to inspect affected structural
SupportPC12@pilatus-aircraft.com; Internet: email: airworthiness.A330-A340@ parts in the cargo compartment to
www.pilatus-aircraft.com. airbus.com; Internet: http:// determine if proper heat treatment has
(4) You may view this service information www.airbus.com. You may view this been done, and replacement of parts;
at the FAA, Small Airplane Directorate, 901 referenced service information at the and
Locust, Kansas City, Missouri 64106. For FAA, Transport Airplane Directorate,
information on the availability of this • Airbus Service Bulletin A330–53–
1601 Lind Avenue SW., Renton, WA. 3228, dated August 18, 2015. The
material at the FAA, call (816) 329–4148. In
addition, you can access this service For information on the availability of service information describes
information on the Internet at http:// this material at the FAA, call 425–227– procedures to inspect affected structural
www.regulations.gov by searching for and 1221. It is also available on the Internet parts in the cabin compartment to
locating Docket No. FAA–2016–7048. at http://www.regulations.gov by determine if proper heat treatment has
(5) You may view this service information searching for and locating Docket No. been done, and replacement of parts.
that is incorporated by reference at the FAA–2016–5460.
National Archives and Records This service information is reasonably
Administration (NARA). For information on Examining the AD Docket available because the interested parties
the availability of this material at NARA, call
You may examine the AD docket on have access to it through their normal
202–741–6030, or go to: http:// course of business or by the means
www.archives.gov/federal-register/cfr/ibr- the Internet at http://
www.regulations.gov; or in person at the identified in the ADDRESSES section.
locations.html.
Docket Management Facility between 9 Correction of Publication
Issued in Kansas City, Missouri, on August a.m. and 5 p.m., Monday through
23, 2016. This document corrects two errors
Friday, except Federal holidays. The AD
David R. Showers, docket contains this AD, the regulatory and correctly adds the AD as an
Acting Manager, Small Airplane Directorate, evaluation, any comments received, and amendment to 14 CFR 39.13. Although
Aircraft Certification Service. other information. The address for the no other part of the preamble or
[FR Doc. 2016–20833 Filed 8–31–16; 8:45 am] Docket Office (phone: 800–647–5527) is regulatory information has been
BILLING CODE 4910–13–P Docket Management Facility, U.S. corrected, we are publishing the entire
Department of Transportation, Docket rule in the Federal Register.
Operations, M–30, West Building The effective date of this AD remains
DEPARTMENT OF TRANSPORTATION Ground Floor, Room W12–140, 1200 September 8, 2016.
Federal Aviation Administration New Jersey Avenue SE., Washington, Since this action only corrects a
DC 20590. typographical error in two locations, it
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: has no adverse economic impact and
Vladimir Ulyanov, Aerospace Engineer, imposes no additional burden on any
[Docket No. FAA–2016–5460; Directorate International Branch, ANM–116, person. Therefore, we have determined
Identifier 2015–NM–188–AD; Amendment Transport Airplane Directorate, FAA, that notice and public procedures are
39–18599; AD 2016–16–01] unnecessary.
1601 Lind Avenue SW., Renton, WA
RIN 2120–AA64 98057–3356; telephone: 425–227–1138; List of Subjects in 14 CFR Part 39
fax: 425–227–1149.
Airworthiness Directives; Airbus SUPPLEMENTARY INFORMATION: Air transportation, Aircraft, Aviation
Airplanes Airworthiness Directive 2016–16–01, safety, Incorporation by reference,
AGENCY: Federal Aviation Amendment 39–18599 (81 FR 51325, Safety.
Administration (FAA), DOT. August 4, 2016) (‘‘AD 2016–16–01’’), Adoption of the Correction
ACTION: Final rule; correction. currently requires an inspection of
affected structural parts in the cargo and Accordingly, pursuant to the
SUMMARY: The FAA is correcting an cabin compartments to determine if authority delegated to me by the
airworthiness directive (AD) that proper heat treatment has been done, Administrator, the Federal Aviation
published in the Federal Register. That and replacement if necessary, for certain Administration amends part 39 of the
AD applies to certain Airbus Model Airbus Model A330–200 Freighter, Federal Aviation Regulations (14 CFR
asabaliauskas on DSK3SPTVN1PROD with RULES
A330–200 Freighter, –200, and –300 –200, and –300 series airplanes. part 39) as follows:
series airplanes. Paragraphs (i) and (l) of
the regulatory text contain Need for the Correction PART 39—AIRWORTHINESS
typographical errors in the service As published, paragraphs (i) and (l) of DIRECTIVES
bulletin number. This document the regulatory text identify the service
corrects those errors. In all other information by the wrong service ■ 1. The authority citation for part 39
respects, the original document remains bulletin number. Where paragraphs (i) continues to read as follows:
the same. and (l) incorrectly specify Airbus Authority: 49 U.S.C. 106(g), 40113, 44701.
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Document Created: 2018-02-09 11:57:05
Document Modified: 2018-02-09 11:57:05
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 6, 2016. | |
| Contact | Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: [email protected] | |
| FR Citation | 81 FR 60243 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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