Airworthiness Directives; Pilatus Aircraft LTD. Airplanes, 48701-48703 [2014-19490]

Download as PDF Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0594; Directorate Identifier 2014–CE–022–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft LTD. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all PILATUS AIRCRAFT LTD. Models PC– 12, PC–12/45, PC–12/47, and PC–12/ 47E airplanes that would supersede AD 2012–26–16. This proposed AD results from 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 a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). We are issuing this proposed AD to require actions to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 2, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Pilatus Aircraft LTD., Customer Service Manager, CH–6371 STANS, Switzerland; telephone: +41 (0) 41 619 33 33; fax: +41 (0) 41 619 73 11; Internet: http://www.pilatusaircraft.com or email: SupportPC12@ pilatus-aircraft.com. You may review copies of the referenced service information at the FAA, Small Airplane tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:52 Aug 15, 2014 Jkt 232001 Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. 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–2014– 0594; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0594; Directorate Identifier 2014–CE–022–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On February 8, 2013, we issued AD 2012–26–16, Amendment 39–17311 (78 FR 11572, February 19, 2013). That AD required actions intended to address an unsafe condition on all Pilatus Aircraft LTD. Models PC–12, PC–12/45, PC–12/ 47, and PC–12/47E airplanes and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. Since we issued AD 2012–26–16, Amendment 39–17311 (78 FR 11572, PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 48701 February 19, 2013), Pilatus Aircraft LTD. has issued revisions to the Limitations section of the airplane maintenance manual to include repetitive inspections of the inboard flap drive arms for cracks. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2014– 0170, dated July 17, 2014 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The maintenance instructions and airworthiness limitations applicable to the Structure and Components of PC–12 aeroplanes are specified in the Aircraft Maintenance Manual (AMM) under Chapter 4, Airworthiness Limitation Section (ALS). The instructions contained in the ALS document have been identified as mandatory actions for continued airworthiness and failure to comply with these instructions and limitations could potentially lead to an unsafe condition. Pilatus Aircraft Ltd. recently issued Pilatus PC–12 AMM report 02049 issue 28 for PC– 12, PC–12/45 and PC–12/47 aeroplanes and PC–12 AMM report 02300 issue 11 for PC– 12/47E aeroplanes to incorporate new repetitive inspection intervals of the inboard flap drive arms because of the detection of cracked parts. For the reason described above, this AD retains the requirements of EASA AD 2013– 0031, which is superseded, and requires implementation of the new maintenance requirements and/or airworthiness limitations. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0594. Relevant Service Information Pilatus Aircraft LTD. has issued Structural, Component and Miscellaneous—Airworthiness Limitations, document 12–A–04–00– 00–00A–000A–A, dated March 13, 2014, and Structural and Component Limitations—Airworthiness Limitations, document 12–B–04–00–00–00A–000A– A, dated March 13, 2014. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all E:\FR\FM\18AUP1.SGM 18AUP1 48702 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules tkelley on DSK3SPTVN1PROD with PROPOSALS information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this AD will affect 770 products of U.S. registry. We also estimate that it would take about 16.5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $300 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $1,310,925, or $1,702.50 per product. This breaks down as follows: • New inspections, etc. through incorporating maintenance manual limitations: 3.5 work-hours with parts about $300 for a fleet cost of $460,075, or $597.50 per product. • Wing main spar fastener holes inspection: 12 work-hours with no parts cost for fleet cost of $785,400 or $1,020 per product. • Inboard flap drive arm inspection: 1 work-hour with no parts cost for fleet cost of $65,450 or $85 per product. In addition, we estimate that any necessary corrective actions (oncondition costs) that must be taken based on the above inspections, etc. would take about 16 work-hours and require parts costing approximately $10,000 for a cost of $11,360 per product. We have no way of determining the number of products that may need these necessary corrective actions. This breaks down as follows: • Replacements based on damaged parts or reduced life limits as a result of the new maintenance manual limitations: 6 work-hours with parts about $4,000 for a cost of $4,510 per product. • Repairs to the wing spar as a result of the wing main spar fastener holes inspection: 7 work-hours with parts about $5,000 for a cost of $5,595 per product. • Replacement of the inboard flap drive arm as a result of the inboard flap drive arm inspection: 3 work-hours with parts about $1,000 for a cost of $1,255. The only costs that would be imposed by this proposed AD over that already required by AD 2012–26–16 is the inboard flap arm inspection and replacement as necessary and the addition of 92 airplanes from 678 airplanes to 770 airplanes. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Mar<15>2010 16:52 Aug 15, 2014 Jkt 232001 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 proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 removing Amendment 39–17311 (78 FR ■ PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 11572, February 19, 2013), and adding the following new AD: Pilatus Aircraft LTD.: Docket No. FAA– 2014–0594; Directorate Identifier 2014– CE–022–AD. (a) Comments Due Date We must receive comments by October 2, 2014. (b) Affected ADs This AD supersedes AD 2012–26–16, Amendment 39–17311 (78 FR 11572, February 19, 2013). (c) Applicability This AD applies to PILATUS AIRCRAFT LTD. Models PC–12, PC–12/45, PC–12/47, and PC–12/47E airplanes, all manufacturer serial numbers (MSNs), certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 5: Time Limits. (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 a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAAapproved maintenance program (e.g., maintenance manual). The limitations were revised to include repetitive inspections of the inboard flap drive arms for crack(s). These actions are required to ensure the continued operational safety of the affected airplanes. (f) Actions and Compliance Unless already done, do the following actions in paragraphs (f)(1) through (f)(7) of this AD: (1) Actions retained from AD 2012–26–16, Amendment 39–17311 (78 FR 11572, February 19, 2013) for Models PC–12 and PC–12/45 airplanes, MSNs 101 through 299: Within the next 100 hours time-in-service (TIS) after August 19, 2009 (the effective date retained from AD 2009–14–13, Amendment 39–15963 (74 FR 34213, July 15, 2009)) or 1 year after August 19, 2009 (the effective date retained from AD 2009–14–13), whichever occurs first, replace the torque tube part number (P/N) 532.50.12.047 with torque tube P/N 532.50.12.064 following Pilatus Aircraft LTD. Service Bulletin No: 32–021, dated November 21, 2008. (2) Actions retained from AD 2012–26–16, Amendment 39–17311 (78 FR 11572, February 19. 2013) for all airplanes: As of March 26, 2013 (the effective date retained from AD 2012–26–16), do not install torque tube P/N 532.50.12.047. (3) Actions new to this AD for all airplanes: Before further flight after September 22, 2014 (the effective date of this AD), insert Data module code 12–A–04–00–00–00A–000A–A, ‘‘Structural, Component and Miscellaneous— Airworthiness Limitations,’’ dated March 13, 2014, of the Pilatus Model Identification: 12 Aircraft Maintenance Manual, PC12, PC12/ E:\FR\FM\18AUP1.SGM 18AUP1 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules tkelley on DSK3SPTVN1PROD with PROPOSALS 45, PC 12/47 AMM Document No. 02049, 12– A–AM–00–00–00–I, revision 28, dated May 31, 2014, for Models PC–12, PC–12/45, PC– 12/47, and Data module code 12–B–04–00– 00–00A–000A–A, ‘‘Structural and Component Limitations—Airworthiness Limitations,’’ dated March 13, 2014, of the Pilatus Model Identification: 12 Aircraft Maintenance Manual, PC 12/47E AMM Document No. 02300, 12–B–AM–00–00–00– I, revision 11, dated May 31, 2014, for Model PC–12/47E, into the Limitations section of the FAA-approved maintenance program (e.g., maintenance manual). These limitations section revisions do the following: (i) Establish an inspection of the inboard flap drive arms, (ii) Specify replacement of components before or upon reaching the applicable life limit, and (iii) Specify accomplishment of all applicable maintenance tasks within certain thresholds and intervals. (4) Actions retained from AD 2012–26–16, Amendment 39–17311 (78 FR 11572, February 19. 2013) for all airplanes: Only authorized Pilatus Service Centers can do the Supplemental Structural Inspection Document (SSID) as required by the documents in paragraph (f)(3) of this AD because deviations from the type design in critical locations could make the airplane ineligible for this life extension. (5) Actions new to this AD for all airplanes: If no compliance time is specified in the documents listed in paragraph (f)(3) of this AD when doing any corrective actions where discrepancies are found as required in paragraph (f)(3)(iii) of this AD, do these corrective actions before further flight after doing the applicable maintenance task. (6) Actions new to this AD for all airplanes: During the accomplishment of the actions required in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of this AD, if a discrepancy is found that is not identified in the documents listed in paragraph (f)(3) of this AD, before further flight after finding the discrepancy, contact Pilatus Aircraft LTD, at the address specified in paragraph (i) of this AD for a repair scheme and incorporate that repair scheme. (7) Actions new to this AD for all airplanes: Within the next 3 months after the effective date of this AD or within the next 150 hours TIS after the effective date of this AD, whichever occurs first, inspect the inboard flap drive arms for cracks and take all necessary corrective actions. (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 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. (i) 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 VerDate Mar<15>2010 16:52 Aug 15, 2014 Jkt 232001 Office (FSDO), or lacking a PI, your local FSDO. (ii) AMOCs approved for AD 2012–26–16, Amendment 39–17311 (77 FR 11572, February 19, 2013) are not approved as AMOCs for this AD. (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) Special Flight Permit Special flight permits are prohibited. (i) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2014–0170, dated July 17, 2014, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0594. For service information related to this AD, contact Pilatus Aircraft LTD., Customer Service Manager, CH–6371 STANS, Switzerland; telephone: +41 (0) 41 619 33 33; fax: +41 (0) 41 619 73 11; Internet: http:// www.pilatus-aircraft.com or email: SupportPC12@pilatus-aircraft.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on August 12, 2014. Monica L. Nemecek, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–19490 Filed 8–15–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0570; Directorate Identifier 2013–NM–094–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes. This proposed AD was prompted by fuel system reviews conducted by the manufacturer. This SUMMARY: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 48703 proposed AD would require revising the maintenance or inspection program to incorporate new limitations for fuel tank systems. We are proposing this AD to prevent potential ignition sources within the fuel system, which could result in a fuel tank explosion. DATES: We must receive comments on this proposed AD by October 2, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.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. 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–2014– 0570; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Morton Lee, Propulsion Engineer, Propulsion & Services Branch, ANE– 173; FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7355; fax 516–794–5531. E:\FR\FM\18AUP1.SGM 18AUP1

Agencies

[Federal Register Volume 79, Number 159 (Monday, August 18, 2014)]
[Proposed Rules]
[Pages 48701-48703]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-19490]



[[Page 48701]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0594; Directorate Identifier 2014-CE-022-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft LTD. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E 
airplanes that would supersede AD 2012-26-16. This proposed AD results 
from 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 a need to incorporate new revisions into the Limitations 
section, Chapter 4, of the FAA-approved maintenance program (e.g., 
maintenance manual). We are issuing this proposed AD to require actions 
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by October 2, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Pilatus Aircraft LTD., Customer Service Manager, CH-6371 STANS, 
Switzerland; telephone: +41 (0) 41 619 33 33; fax: +41 (0) 41 619 73 
11; Internet: http://www.pilatus-aircraft.com or email: 
aircraft.com">SupportPC12@pilatus-aircraft.com. You may review copies of the 
referenced service information at the FAA, Small Airplane Directorate, 
901 Locust, Kansas City, Missouri 64106. For information on the 
availability of this material at the FAA, call (816) 329-4148.

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-2014-
0594; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone (800) 647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: 
doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0594; 
Directorate Identifier 2014-CE-022-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On February 8, 2013, we issued AD 2012-26-16, Amendment 39-17311 
(78 FR 11572, February 19, 2013). That AD required actions intended to 
address an unsafe condition on all Pilatus Aircraft LTD. Models PC-12, 
PC-12/45, PC-12/47, and PC-12/47E airplanes and was based on mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country.
    Since we issued AD 2012-26-16, Amendment 39-17311 (78 FR 11572, 
February 19, 2013), Pilatus Aircraft LTD. has issued revisions to the 
Limitations section of the airplane maintenance manual to include 
repetitive inspections of the inboard flap drive arms for cracks.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2014-0170, dated July 17, 2014 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    The maintenance instructions and airworthiness limitations 
applicable to the Structure and Components of PC-12 aeroplanes are 
specified in the Aircraft Maintenance Manual (AMM) under Chapter 4, 
Airworthiness Limitation Section (ALS).
    The instructions contained in the ALS document have been 
identified as mandatory actions for continued airworthiness and 
failure to comply with these instructions and limitations could 
potentially lead to an unsafe condition.
    Pilatus Aircraft Ltd. recently issued Pilatus PC-12 AMM report 
02049 issue 28 for PC-12, PC-12/45 and PC-12/47 aeroplanes and PC-12 
AMM report 02300 issue 11 for PC-12/47E aeroplanes to incorporate 
new repetitive inspection intervals of the inboard flap drive arms 
because of the detection of cracked parts.
    For the reason described above, this AD retains the requirements 
of EASA AD 2013-0031, which is superseded, and requires 
implementation of the new maintenance requirements and/or 
airworthiness limitations.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2014-0594.

Relevant Service Information

    Pilatus Aircraft LTD. has issued Structural, Component and 
Miscellaneous--Airworthiness Limitations, document 12-A-04-00-00-00A-
000A-A, dated March 13, 2014, and Structural and Component 
Limitations--Airworthiness Limitations, document 12-B-04-00-00-00A-
000A-A, dated March 13, 2014. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all

[[Page 48702]]

information and determined the unsafe condition exists and is likely to 
exist or develop on other products of the same type design.

Costs of Compliance

    We estimate that this AD will affect 770 products of U.S. registry. 
We also estimate that it would take about 16.5 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $300 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $1,310,925, or $1,702.50 per 
product. This breaks down as follows:
     New inspections, etc. through incorporating maintenance 
manual limitations: 3.5 work-hours with parts about $300 for a fleet 
cost of $460,075, or $597.50 per product.
     Wing main spar fastener holes inspection: 12 work-hours 
with no parts cost for fleet cost of $785,400 or $1,020 per product.
     Inboard flap drive arm inspection: 1 work-hour with no 
parts cost for fleet cost of $65,450 or $85 per product.
    In addition, we estimate that any necessary corrective actions (on-
condition costs) that must be taken based on the above inspections, 
etc. would take about 16 work-hours and require parts costing 
approximately $10,000 for a cost of $11,360 per product. We have no way 
of determining the number of products that may need these necessary 
corrective actions. This breaks down as follows:
     Replacements based on damaged parts or reduced life limits 
as a result of the new maintenance manual limitations: 6 work-hours 
with parts about $4,000 for a cost of $4,510 per product.
     Repairs to the wing spar as a result of the wing main spar 
fastener holes inspection: 7 work-hours with parts about $5,000 for a 
cost of $5,595 per product.
     Replacement of the inboard flap drive arm as a result of 
the inboard flap drive arm inspection: 3 work-hours with parts about 
$1,000 for a cost of $1,255.
    The only costs that would be imposed by this proposed AD over that 
already required by AD 2012-26-16 is the inboard flap arm inspection 
and replacement as necessary and the addition of 92 airplanes from 678 
airplanes to 770 airplanes.

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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 removing Amendment 39-17311 (78 FR 
11572, February 19, 2013), and adding the following new AD:

Pilatus Aircraft LTD.: Docket No. FAA-2014-0594; Directorate 
Identifier 2014-CE-022-AD.

(a) Comments Due Date

    We must receive comments by October 2, 2014.

(b) Affected ADs

    This AD supersedes AD 2012-26-16, Amendment 39-17311 (78 FR 
11572, February 19, 2013).

(c) Applicability

    This AD applies to PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, 
PC-12/47, and PC-12/47E airplanes, all manufacturer serial numbers 
(MSNs), certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 5: Time Limits.

(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 a need to 
incorporate new revisions into the Limitations section, Chapter 4, 
of the FAA-approved maintenance program (e.g., maintenance manual). 
The limitations were revised to include repetitive inspections of 
the inboard flap drive arms for crack(s). These actions are required 
to ensure the continued operational safety of the affected 
airplanes.

(f) Actions and Compliance

    Unless already done, do the following actions in paragraphs 
(f)(1) through (f)(7) of this AD:
    (1) Actions retained from AD 2012-26-16, Amendment 39-17311 (78 
FR 11572, February 19, 2013) for Models PC-12 and PC-12/45 
airplanes, MSNs 101 through 299: Within the next 100 hours time-in-
service (TIS) after August 19, 2009 (the effective date retained 
from AD 2009-14-13, Amendment 39-15963 (74 FR 34213, July 15, 2009)) 
or 1 year after August 19, 2009 (the effective date retained from AD 
2009-14-13), whichever occurs first, replace the torque tube part 
number (P/N) 532.50.12.047 with torque tube P/N 532.50.12.064 
following Pilatus Aircraft LTD. Service Bulletin No: 32-021, dated 
November 21, 2008.
    (2) Actions retained from AD 2012-26-16, Amendment 39-17311 (78 
FR 11572, February 19. 2013) for all airplanes: As of March 26, 2013 
(the effective date retained from AD 2012-26-16), do not install 
torque tube P/N 532.50.12.047.
    (3) Actions new to this AD for all airplanes: Before further 
flight after September 22, 2014 (the effective date of this AD), 
insert Data module code 12-A-04-00-00-00A-000A-A, ``Structural, 
Component and Miscellaneous--Airworthiness Limitations,'' dated 
March 13, 2014, of the Pilatus Model Identification: 12 Aircraft 
Maintenance Manual, PC12, PC12/

[[Page 48703]]

45, PC 12/47 AMM Document No. 02049, 12-A-AM-00-00-00-I, revision 
28, dated May 31, 2014, for Models PC-12, PC-12/45, PC-12/47, and 
Data module code 12-B-04-00-00-00A-000A-A, ``Structural and 
Component Limitations--Airworthiness Limitations,'' dated March 13, 
2014, of the Pilatus Model Identification: 12 Aircraft Maintenance 
Manual, PC 12/47E AMM Document No. 02300, 12-B-AM-00-00-00-I, 
revision 11, dated May 31, 2014, for Model PC-12/47E, into the 
Limitations section of the FAA-approved maintenance program (e.g., 
maintenance manual). These limitations section revisions do the 
following:
    (i) Establish an inspection of the inboard flap drive arms,
    (ii) Specify replacement of components before or upon reaching 
the applicable life limit, and
    (iii) Specify accomplishment of all applicable maintenance tasks 
within certain thresholds and intervals.
    (4) Actions retained from AD 2012-26-16, Amendment 39-17311 (78 
FR 11572, February 19. 2013) for all airplanes: Only authorized 
Pilatus Service Centers can do the Supplemental Structural 
Inspection Document (SSID) as required by the documents in paragraph 
(f)(3) of this AD because deviations from the type design in 
critical locations could make the airplane ineligible for this life 
extension.
    (5) Actions new to this AD for all airplanes: If no compliance 
time is specified in the documents listed in paragraph (f)(3) of 
this AD when doing any corrective actions where discrepancies are 
found as required in paragraph (f)(3)(iii) of this AD, do these 
corrective actions before further flight after doing the applicable 
maintenance task.
    (6) Actions new to this AD for all airplanes: During the 
accomplishment of the actions required in paragraphs (f)(3)(i), 
(f)(3)(ii), and (f)(3)(iii) of this AD, if a discrepancy is found 
that is not identified in the documents listed in paragraph (f)(3) 
of this AD, before further flight after finding the discrepancy, 
contact Pilatus Aircraft LTD, at the address specified in paragraph 
(i) of this AD for a repair scheme and incorporate that repair 
scheme.
    (7) Actions new to this AD for all airplanes: Within the next 3 
months after the effective date of this AD or within the next 150 
hours TIS after the effective date of this AD, whichever occurs 
first, inspect the inboard flap drive arms for cracks and take all 
necessary corrective actions.

(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 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.
    (i) 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.
    (ii) AMOCs approved for AD 2012-26-16, Amendment 39-17311 (77 FR 
11572, February 19, 2013) are not approved as AMOCs for this AD.
    (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) Special Flight Permit

    Special flight permits are prohibited.

(i) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2014-0170, dated July 17, 2014, for related information. You may 
examine the MCAI on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0594. For service 
information related to this AD, contact Pilatus Aircraft LTD., 
Customer Service Manager, CH-6371 STANS, Switzerland; telephone: +41 
(0) 41 619 33 33; fax: +41 (0) 41 619 73 11; Internet: http://
www.pilatus-aircraft.com or email: aircraft.com">SupportPC12@pilatus-aircraft.com. 
You may review copies of the referenced service information at the 
FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
FAA, call (816) 329-4148.

     Issued in Kansas City, Missouri, on August 12, 2014.
Monica L. Nemecek,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-19490 Filed 8-15-14; 8:45 am]
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