AD 2016-12-01

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. 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 incorrect installation instructions of the torlon plates in the airplane maintenance manual resulting in the incorrect installation of the torlon plates in the forward wing-to-fuselage attachment. We are issuing this AD to require actions to address the unsafe condition on these products.

Final rule.

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:

2016-12-01 Pilatus Aircraft LTD.: Amendment 39-18550; Docket No. FAA-2016-5284; Directorate Identifier 2016-CE-006-AD.

(a) Effective Date

This airworthiness directive (AD) becomes effective July 15, 2016.

(b) Affected ADs

None.

(c) Applicability

This AD applies to PILATUS AIRCRAFT LTD. PC-12, PC-12/45, PC-12/ 47, and PC-12/47E airplanes, all serial numbers delivered before January 1, 2015, certificated in any category.
Note 1 to paragraph (c) of this AD: The date of delivery may be found as the issue date of the EASA Form 52, which is part of theairplane records.

(d) Subject

Air Transport Association of America (ATA) Code 57: Wings.

(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 incorrect installation instructions of the torlon plates in the airplane maintenance manual resulting in the incorrect installation of the torlon plates in the forward wing-to-fuselage attachment. We are issuing this AD to identify and correct incorrectly installed torlon plates which could cause additional loads affecting the fatigue life at the wing-to-fuselage interface.

(f) Actions and Compliance

Do the actions in paragraphs (f)(1) through (4) of this AD. If paragraphs (f)(1), (2), and (3) of this AD have already been done before July 15, 2016 (the effective date of this AD), then only paragraph (f)(4) of this AD applies.

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(1) For any airplane that has had a wing removed and reinstalled or replaced between June 2007 and July 15, 2016 (the effective date of this AD): Within the next 12 months after July 15, 2016 (the effective date of this AD), inspect the torlon plates in the forward lower wing-to-fuselage attachments (both left hand (LH) and right hand (RH) sides) for correct installation following the accomplishment instructions in PILATUS AIRCRAFT LTD. PC-12 Service Bulletin No: 57-007, dated September 29, 2015.
(2) For any airplane that has had a wing removed and reinstalled or replaced, between June 2007 and July 15, 2016 (the effective date of this AD): If an incorrect installation of the torlon plates is found during the inspection required in paragraph (f)(1) of this AD, remove the affected torlon plates, visually inspect the torlon plates and the affected lugs using a mirror and light source (if necessary) for any damage, and reinstall the torlon plates inthe correct sequence, following the accomplishment instructions in paragraph 3.C. of PILATUS AIRCRAFT LTD. PC-12 Service Bulletin No: 57-007, dated September 29, 2015.
(3) For any airplane that has had a wing removed and reinstalled or replaced, between June 2007 and July 15, 2016 (the effective date of this AD): If any damage is found during the inspection of the torlon plates and lugs required in paragraph (f)(2) of this AD, before further flight, contact PILATUS AIRCRAFT LTD. for FAA- approved repair instructions and accomplish those instructions accordingly. You may find contact information for PILATUS AIRCRAFT LTD. in paragraph (h) of this AD.
(4) For all airplanes: As of July 15, 2016 (the effective date of this AD), do not install or re-install a wing on any airplane, unless concurrent with the wing installation, the torlon plates of the forward lower wing-to-fuselage attachment (both LH and RH sides) of the airplane are inspected and found to be installed correctly in accordance with the accomplishment instructions in paragraph 3.B. of PILATUS AIRCRAFT LTD. PC-12 Service Bulletin No: 57-007, dated September 29, 2015.

Note 2 to paragraph (f)(4) of this AD: Installation of a wing on an airplane in accordance with the instructions of PILATUS aircraft maintenance manual (AMM) 02049, Revision 28 or later, or AMM 02300, Revision 11 or later, is an acceptable alternative method to comply with this inspection requirement.

(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 MCAI European Aviation Safety Agency (EASA) AD No.: 2016-0037, dated February 26, 2016, for related information. The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/#!documentDetail;D=FAA-2016-5284-0002.

(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-12 Service Bulletin No: 57-007, dated September 29, 2015.
(ii) Reserved.
(3) For PILATUS AIRCRAFT LTD. service information identified in this AD, contact PILATUS AIRCRAFT LTD., Customer Support Manager, CH-6371 STANS, Switzerland; phone: +41 (0)41 619 33 33; fax: +41 (0)41 619 73 11; email: aircraft.com">SupportPC12@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. In addition, you can access this service information on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5284.
(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.

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. The NPRM was published in the Federal Register on March 28, 2016 (81 FR 17107). 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:

Incorrect installations of torlon plates in the forward lower wing-to-fuselage attachment were reported on aeroplanes in service. Investigation determined that wrong torlon plate installation instructions were published in June 2007 in Revision (Rev.) 18 to 27 of the Aircraft Maintenance Manual (AMM) 02049, Data Module (DM) 12- A-57-00-00A-520A-A and DM 12-A-57-00-00A-720A-A, for the PC-12, PC- 12/45 and PC-12/47 aeroplanes, and in the initial issueto Rev. 10 of AMM 02300, in DM 12-B-57-00-00A-520A-A and DM 12-B-57-00-00A- 720A-A, for PC-12/47E aeroplanes.
This condition, if not corrected, could lead to additional loads at the wing-to-fuselage interface, which detrimentally affects the fatigue life of the structural joint.
To address this potential unsafe condition, Pilatus issued Service Bulletin (SB) No. 57-007 to provide inspection instructions to verify the correct installation of torlon plates in the wing-to- fuselage attachments, and the rectification instructions for incorrect installed torlon plates.
For the reason described above, this AD requires a one-time inspection of the forward lower wing-to-fuselage attachments, both left hand (LH) and right hand (RH) sides and, depending on findings, accomplishment of applicable corrective action(s).

The MCAI can be found in the AD docket on the Internet at: https://

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www.regulations.gov/#!documentDetail;D=FAA-2016-5284-0002.

CommentsWe gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (81 FR 17107, March 28, 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 17107, March 28, 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 17107, March 28, 2016).

Related Service Information Under 1 CFR Part 51

We reviewed PILATUS AIRCRAFT LTD. PC-12 Service Bulletin No: 57- 007, dated September 29, 2015. The service information describes procedures for inspection, and if necessary realignment or replacement of the torlon plates in the forward lower wing-to-fuselage attachments. 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 268 products of U.S. registry. We also estimate that it would take about 1 work-hour per wing 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 the AD on U.S. operators to be $45,560, or $170 per product.
In addition, we estimate that any necessary follow-on actions would take about 3 work-hours per wing and require parts costing $1,000 per wing, for a total cost of $2,510 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 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- 5284; 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.