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Proposed Rule

Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

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Start Preamble

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 PILATUS Aircraft Ltd. Model PC-7 airplanes. 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 possible cracking from stress corrosion on various parts of the aircraft structure made of aluminum alloy AA2024-T351. 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 November 21, 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 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. You may review 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.

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-2014-0770; 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.

Start Further Info

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.

End Further Info End Preamble Start Supplemental Information

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-2014-0770; Directorate Identifier 2014-CE-024-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

The Federal Office of Civil Aviation (FOCA), which is the aviation authority for Switzerland, has issued AD HB-2014-001, dated July 25, 2014 (referred to after this as “the MCAI”), to correct an unsafe condition for PILATUS Aircraft Ltd. Model PC-7 airplanes and was based on mandatory continuing airworthiness information originated by an aviation authority of another country. The MCAI states:

This Airworthiness Directive (AD) is prompted due to the possibility of cracks in Start Printed Page 60390some critical parts. It is possible that stress corrosion cracks may occur on various parts of the aircraft structure initially made of aluminium alloy AA2024-T351 which is susceptible to Stress Corrosion Cracking (SCC). Later in production, the material specification was changed to aluminium alloy AA2124-T851 to decrease the risk of stress corrosion. The Part Number (P/N) of the affected structural parts are not always changed when the new material was introduced.

Such a condition, if left uncorrected, could lead to failure of critical parts on the aircraft structure and will prejudice the structural integrity of the aircraft.

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 aluminium 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 also requires replacement of the elevator center control-rod, P/N 116.35.07.271 or 116.35.07.345; and shackle, P/N 116.35.07.183. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0770.

Relevant Service Information

PILATUS Aircraft Ltd. has issued PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. PILATUS PC-7 Service Bulletin No: 51-001 was revised to Revision No. 1 after the issuance of 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 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 proposed AD will affect 10 products of U.S. registry. We also estimate that it would take about 30 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 $4,700 per product.

Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $72,500, or $7,250 per product.

In addition, we estimate that any necessary follow-on actions would take about 14 work-hours and require parts costing $10,000, for a cost of $11,190 per product. We have no way of determining the number of products that may need these actions.

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 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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
End List of Subjects

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new AD:

End Amendment Part

PILATUS Aircraft Ltd.: Docket No. FAA-2014-0770; Directorate Identifier 2014-CE-024-AD.

(a) Comments Due Date

We must receive comments by November 21, 2014.

(b) Affected ADs

None.

(c) Applicability

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

(d) Subject

Air Transport Association of America (ATA) Code 51: Standard Practices/Structures.

(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 possible cracking from stress corrosion on various parts of the aircraft structure made of aluminum alloy AA2024-T351. We are issuing this proposed AD to detect and correct stress corrosion cracks that may occur on various parts of the airplane structure initially made of aluminum alloy AA2024-T351, which is susceptible to stress corrosion cracking (SCC). Such a condition, if left uncorrected, could lead to failure of critical parts on the airplane structure and weaken the structural integrity of the aircraft.

(f) Actions and Compliance

Unless already done, within the next 12 months after the effective date of this AD, perform a one-time conductivity test of items 6 through 9 and 11 through 13 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, to check the material of the parts—determine whether they are made of aluminum alloy AA2124-T851 or aluminum alloy AA2024-T351. Do not install any item Start Printed Page 60391unless it has been inspected following the applicable paragraph of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014.

(1) For airplanes with any parts made of aluminum alloy AA2124-T851: Within 12 months after the effective date of this AD, make an entry in the aircraft logbook as required by paragraph 3.D.(3) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014. The only other actions of this AD that apply to airplanes with all parts made of aluminum alloy AA2124-T851 are the actions in paragraphs (f)(3), (f)(4), and (f)(5) of this AD.

(2) For airplanes with any parts made of aluminum alloy AA2024-T351: Within 12 months after the effective date of this AD, do the actions in paragraphs (f)(2)(i) through (f)(2)(iii) as applicable, including all subparagraphs:

(i) For items 7 through 9 and 11 through 13 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after the effective date of this AD, do a one-time inspection for cracks. If any cracks are found as a result of the inspection, before further flight, you must contact PILATUS Aircraft Ltd. to obtain FAA-approved repair instructions approved specifically for compliance with this AD and incorporate those instructions. Use the contact information found in paragraph (h) of this AD.

(ii) For item 6 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after the effective date of this AD, replace with a part made of aluminum alloy AA2124-T851.

(iii) For Items 1, 2, 4, 5, and 10 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after the effective date of this AD, do the following actions in paragraphs (f)(2)(iii)(A) and (f)(2)(iii)(B), as applicable.

(A) For items 1, 2, 4, and 10 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, do a one-time inspection for cracks. If any cracks are found, before further flight, you must contact PILATUS Aircraft Ltd. to obtain FAA-approved repair instructions approved specifically for compliance with this AD and incorporate those instructions. Use the contact information found in paragraph (h) of this AD.

(B) For item 5 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, replace with a part made of aluminum alloy AA2124-T851.

(3) For all airplanes: For item 3 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after the effective date of this AD, replace with a part made of aluminum alloy AA2124-T851. You must replace the elevator center control-rods (item 3 as listed in paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014) because it is difficult to inspect them for cracks.

(4) For all airplanes: As of 12 months after the effective date of this AD, do not install the parts listed in items 1 and 2, 4, and 7 through 13 of paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, that are made of aluminum alloy AA2024-T351 unless they have been inspected and found free of cracks.

(5) For all airplanes: As of 12 months after the effective date of this AD, do not install the parts listed in items 3, 5, and 6 of paragraph 1.A.(2) of PILATUS PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, that are made of aluminum alloy AA2024-T351.

(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-2014-001, dated July 25, 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-2014-0770. For service information related to 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. You may review 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.

Start Signature

Issued in Kansas City, Missouri, on September 30, 2014.

Earl Lawrence,

Manager, Small Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2014-23880 Filed 10-6-14; 8:45 am]

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