Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes, 58811-58813 [2016-20074]

Download as PDF Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations the commodity board is willing to cofund that application, if it is evaluated by the review panel as being meritorious and recommended for award. Done at Washington, DC, this 29 day of July, 2016. Robert E. Holland, Associate Director for Operations, National Institute of Food and Agriculture. [FR Doc. 2016–18422 Filed 8–25–16; 8:45 am] BILLING CODE 3410–22–P DEPARTMENT OF TRANSPORTATION 74; fax: +41 (0)41 619 67 73; email: techsupport@pilatus-aircraft.com; Internet: http://www.pilatusaircraft.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA–2016– 7026. FOR FURTHER INFORMATION CONTACT: [Docket No. FAA–2016–7026; Directorate Identifier 2016–CE–016–AD; Amendment 39–18620; AD 2016–17–07] 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: RIN 2120–AA64 Discussion 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. Model PC–7 airplanes. 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 stress corrosion cracking on the main frame on frame 11 left and right fittings. We are issuing this AD to require actions to address the unsafe condition on these products. SUMMARY: This AD is effective September 30, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 30, 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– 7026; 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 Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 67 ehiers on DSK5VPTVN1PROD with RULES DATES: VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 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. Model PC–7 airplanes. The NPRM was published in the Federal Register on June 9, 2016 (81 FR 37166). 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: This Airworthiness Directive (AD) is prompted due to a report of Stress Corrosion Cracking (SCC) on the Main Frame on Frame (FR) 11 left fitting Part Number (P/N) 112.35.07.489 and right fitting P/N 112.35.07.490. Such a condition, if left uncorrected, could lead to potential loss of the horizontal stabilizer. In order to correct and control the situation, this AD requires a one-time check to identify the material specification and inspect the affected areas of the airframe that are made of aluminum alloy AA2024–T351. Any structural parts of the aircraft structure found to be cracked must be reported to Pilatus prior to further flight. The MCAI can be found in the AD docket on the Internet at: https:// www.regulations.gov/ document?D=FAA-2016-7026-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (81 FR 37166, June 9, 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 58811 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 37166, June 9, 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 37166, June 9, 2016). Related Service Information Under 1 CFR Part 51 We reviewed PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–013; and PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–014, both dated February 25, 2016. PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–013, dated February 25, 2016, describes procedures for initial and repetitive inspection of the main frame FR11 left and right fittings for stress corrosion cracking; and PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–014, dated February 25, 2016, describes procedures for replacement of the main frame FR11 left and right fittings when necessary. 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 the AD. Costs of Compliance We estimate that this AD will affect 19 products of U.S. registry. We also estimate that it would take about 3 work-hours per product to check the material specification of the fittings and 11 work-hours per product to inspect the 2014–T351 fittings as required in order 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 $17,765, or $935 per product. In addition, we estimate that any necessary follow-on actions would take about 19 work-hours and require parts costing $5,000 for a cost of $6,615 per product. We have no way of determining the number of products that may need these actions. 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 E:\FR\FM\26AUR1.SGM 26AUR1 58812 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 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. ehiers on DSK5VPTVN1PROD with RULES 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– 7026; 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. VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 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: ■ 2016–17–07 PILATUS Aircraft Ltd.: Amendment 39–18620; Docket No. FAA–2016–7026; Directorate Identifier 2016–CE–016–AD. (a) Effective Date This airworthiness directive (AD) becomes effective September 30, 2016. (b) Affected ADs None. (c) Applicability This AD applies to PILATUS Aircraft Ltd. Model PC–7 airplanes, manufacturer serial numbers (MSN) 101 through 618, certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 53: Fuselage. (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 stress corrosion cracking on the main frame on frame 11 left and right fittings, which can cause potential loss of the horizontal stabilizer. We are issuing this proposed AD to detect and correct stress corrosion cracking on the frame 11 left and right fittings. (f) Actions and Compliance Unless already done, do the actions in paragraphs (f)(1) through (4) of this AD: (1) Within the next 120 days after September 30, 2016 (the effective date of this AD), check the material specification of the Frame (FR) 11 left fitting part number (P/N) 112.35.07.489 and the FR 11 right fitting P/ N 112.35.07.490 following the Accomplishment Instructions in paragraph 3.B. of PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–013, dated February 25, 2016. (2) If fittings made of aluminum alloy AA2124–T851 are found during the inspection required by paragraph (f)(1) of this AD, within 30 days after the inspection or within the next 30 days after September 30, 2016 (the effective date of this AD), whichever occurs later, report the inspection results following the reporting requirements in paragraph 3.D. of PILATUS Aircraft Ltd. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 PC–7 Service Bulletin No: 53–013, dated February 25, 2016. (3) If fittings made of aluminum alloy AA2024–T351 are found during the inspection required by paragraph (f)(1) of this AD, before further flight, and repetitively thereafter at intervals not to exceed 12 months, inspect FR 11 left fitting, P/N 112.35.07.489 and the FR 11 right fitting, P/ N 112.35.07.490, for cracks following the Accomplishment Instructions in paragraph 3.C. of PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–013, dated February 25, 2016. (4) If cracks are found during any inspection required in paragraph (f)(3) of this AD, before further flight, replace the fittings following the Accomplishment Instructions in paragraph 3 of PILATUS Aircraft Ltd. PC– 7 Service Bulletin No: 53–014, dated February 25, 2016. (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. (3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (h) Related Information Refer to Federal Office of Civil Aviation (FOCA) AD HB–2016–001, dated May 17, E:\FR\FM\26AUR1.SGM 26AUR1 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 2016, for related information. The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/document?D= FAA–2016–7026–0002. (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 Aircraft Ltd. PC–7 Service Bulletin No: 53–013; dated February 25, 2016; and (ii) PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–014, dated February 25, 2016. (3) For PILATUS Aircraft Ltd. service information identified in this AD, contact PILATUS Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 73; email: techsupport@pilatus-aircraft.com; Internet: http://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. (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/ibrlocations.html. Issued in Kansas City, Missouri, on August 17, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20074 Filed 8–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8992; Directorate Identifier 2016–CE–021–AD; Amendment 39–18621; AD 2016–17–08] RIN 2120–AA64 Airworthiness Directives; Textron Aviation, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ehiers on DSK5VPTVN1PROD with RULES AGENCY: We are superseding Airworthiness Directive (AD) 2016–07– 24 for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P SUMMARY: VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 through T310R, 310J–1, 320 through 320F, 320–1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). AD 2016–07–24 required replacement and repetitive inspections of the hardware securing the elevator trim tab push-pull rod. This AD retains the actions for AD 2016–07–24 but revises the repetitive inspection intervals and allows for a longer bolt for the attachment of the elevator trim tab actuator rod end to the push-pull tube connection and/or for the elevator trim tab horn end to the push-pull tube connection. This AD was prompted by comments indicating difficulties with bolt installation and requesting a revision to repetitive inspection intervals to coincide with established inspection intervals. We are issuing this AD to prevent jamming of the elevator trim tab in a position outside the normal limits of travel due to the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, which could result in loss of control. DATES: This AD is effective September 12, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 12, 2016. We must receive any comments on this AD by October 11, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to 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 final rule, contact Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 517–7271; email: customercare@txtav.com; Internet: https://support.cessna.com/custsupt/ csupport/newlogin.jsp. You may review this referenced service information at the FAA, Small Airplane Directorate, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 58813 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8992. 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– 8992; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Adam Hein, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4116; fax: (316) 946–4107; email: adam.hein@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On March 30, 2016, we issued AD 2016–07–24, Amendment 39–18469 (81 FR 21250, April 11, 2016), (‘‘AD 2016– 07–24’’), for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J–1, 320 through 320F, 320–1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). AD 2016– 07–24 required replacing the hardware connecting the elevator trim tab pushpull rod to the elevator trim tab actuator and elevator trim tab. AD 2016–07–24 resulted from accident reports on Textron Aviation, Inc. Models T310Q, 310Q, and 402B airplanes; lessons learned in accident investigation support; and analysis of past accidents. The analysis of National Transportation Safety Board (NTSB) determination of probable cause indicated that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator trim tab may jam in a position outside the normal limits of travel. We issued AD 2016–07–24 to require replacement and repetitive inspections of the hardware securing the elevator trim tab push-pull rod. E:\FR\FM\26AUR1.SGM 26AUR1

Agencies

[Federal Register Volume 81, Number 166 (Friday, August 26, 2016)]
[Rules and Regulations]
[Pages 58811-58813]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20074]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7026; Directorate Identifier 2016-CE-016-AD; 
Amendment 39-18620; AD 2016-17-07]
RIN 2120-AA64


Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for PILATUS 
Aircraft Ltd. Model PC-7 airplanes. 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 stress corrosion cracking on the main frame on frame 11 
left and right fittings. We are issuing this AD to require actions to 
address the unsafe condition on these products.

DATES: This AD is effective September 30, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 30, 
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-
7026; 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 Technical Support (MCC), P.O. Box 992, CH-6371 
Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 
73; email: aircraft.com">techsupport@pilatus-aircraft.com; Internet: http://
www.pilatus-aircraft.com. You may view this referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148. It is also available on the 
Internet at http://www.regulations.gov by searching for Docket No. FAA-
2016-7026.

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. Model 
PC-7 airplanes. The NPRM was published in the Federal Register on June 
9, 2016 (81 FR 37166). 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:

    This Airworthiness Directive (AD) is prompted due to a report of 
Stress Corrosion Cracking (SCC) on the Main Frame on Frame (FR) 11 
left fitting Part Number (P/N) 112.35.07.489 and right fitting P/N 
112.35.07.490.
    Such a condition, if left uncorrected, could lead to potential 
loss of the horizontal stabilizer.
    In order to correct and control the situation, this AD requires 
a one-time check to identify the material specification and inspect 
the affected areas of the airframe that are made of aluminum alloy 
AA2024-T351. Any structural parts of the aircraft structure found to 
be cracked must be reported to Pilatus prior to further flight.

The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/document?D=FAA-2016-7026-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (81 FR 37166, June 9, 
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 37166, June 9, 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 37166, June 9, 2016).

Related Service Information Under 1 CFR Part 51

    We reviewed PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-013; 
and PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-014, both dated 
February 25, 2016. PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-
013, dated February 25, 2016, describes procedures for initial and 
repetitive inspection of the main frame FR11 left and right fittings 
for stress corrosion cracking; and PILATUS Aircraft Ltd. PC-7 Service 
Bulletin No: 53-014, dated February 25, 2016, describes procedures for 
replacement of the main frame FR11 left and right fittings when 
necessary. 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 the AD.

Costs of Compliance

    We estimate that this AD will affect 19 products of U.S. registry. 
We also estimate that it would take about 3 work-hours per product to 
check the material specification of the fittings and 11 work-hours per 
product to inspect the 2014-T351 fittings as required in order 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 $17,765, or $935 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 19 work-hours and require parts costing $5,000 for a cost of 
$6,615 per product. We have no way of determining the number of 
products that may need these actions.
    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

[[Page 58812]]

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-
7026; 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:

2016-17-07 PILATUS Aircraft Ltd.: Amendment 39-18620; Docket No. 
FAA-2016-7026; Directorate Identifier 2016-CE-016-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective September 
30, 2016.

(b) Affected ADs

    None.

 (c) Applicability

    This AD applies to PILATUS Aircraft Ltd. Model PC-7 airplanes, 
manufacturer serial numbers (MSN) 101 through 618, certificated in 
any category.

 (d) Subject

    Air Transport Association of America (ATA) Code 53: Fuselage.

 (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 stress corrosion 
cracking on the main frame on frame 11 left and right fittings, 
which can cause potential loss of the horizontal stabilizer. We are 
issuing this proposed AD to detect and correct stress corrosion 
cracking on the frame 11 left and right fittings.

 (f) Actions and Compliance

    Unless already done, do the actions in paragraphs (f)(1) through 
(4) of this AD:
    (1) Within the next 120 days after September 30, 2016 (the 
effective date of this AD), check the material specification of the 
Frame (FR) 11 left fitting part number (P/N) 112.35.07.489 and the 
FR 11 right fitting P/N 112.35.07.490 following the Accomplishment 
Instructions in paragraph 3.B. of PILATUS Aircraft Ltd. PC-7 Service 
Bulletin No: 53-013, dated February 25, 2016.
    (2) If fittings made of aluminum alloy AA2124-T851 are found 
during the inspection required by paragraph (f)(1) of this AD, 
within 30 days after the inspection or within the next 30 days after 
September 30, 2016 (the effective date of this AD), whichever occurs 
later, report the inspection results following the reporting 
requirements in paragraph 3.D. of PILATUS Aircraft Ltd. PC-7 Service 
Bulletin No: 53-013, dated February 25, 2016.
    (3) If fittings made of aluminum alloy AA2024-T351 are found 
during the inspection required by paragraph (f)(1) of this AD, 
before further flight, and repetitively thereafter at intervals not 
to exceed 12 months, inspect FR 11 left fitting, P/N 112.35.07.489 
and the FR 11 right fitting, P/N 112.35.07.490, for cracks following 
the Accomplishment Instructions in paragraph 3.C. of PILATUS 
Aircraft Ltd. PC-7 Service Bulletin No: 53-013, dated February 25, 
2016.
    (4) If cracks are found during any inspection required in 
paragraph (f)(3) of this AD, before further flight, replace the 
fittings following the Accomplishment Instructions in paragraph 3 of 
PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-014, dated 
February 25, 2016.

 (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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, a federal agency may not conduct or sponsor, and a person 
is not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

 (h) Related Information

    Refer to Federal Office of Civil Aviation (FOCA) AD HB-2016-001, 
dated May 17,

[[Page 58813]]

2016, for related information. The MCAI can be found in the AD 
docket on the Internet at: https://www.regulations.gov/document?D=FAA-2016-7026-0002.

 (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 Aircraft Ltd. PC-7 Service Bulletin No: 53-013; 
dated February 25, 2016; and
    (ii) PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-014, 
dated February 25, 2016.
    (3) For PILATUS Aircraft Ltd. service information identified in 
this AD, contact PILATUS Aircraft Ltd., Customer Technical Support 
(MCC), P.O. Box 992, CH-6371 Stans, Switzerland; phone: +41 (0)41 
619 67 74; fax: +41 (0)41 619 67 73; email: aircraft.com">techsupport@pilatus-aircraft.com; Internet: http://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.
    (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 17, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20074 Filed 8-25-16; 8:45 am]
 BILLING CODE 4910-13-P