Airworthiness Directives: PILATUS Aircraft Ltd. Model PC-7 Airplanes
Federal Register: June 5, 2009 (Volume 74, Number 107)
Proposed Rules
Page 26994-26996
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
DOCID:fr05jn09-18
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2009-0509; Directorate Identifier 2009-CE-029-AD
RIN 2120-AA64
Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7
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 the products listed above. 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:
This Airworthiness Directive (AD) is prompted due to reported corrosion on the
Page 26995
bolts and in the bores of the attachment fittings for the engine mounting frame. The corrosion is caused by damaged cadmium plating of the bolts or damaged surface finish of the attachment fitting.
Such a condition, if left uncorrected, could lead to crack initiation at the bolt and the fitting bore and subsequently to the failure of the engine attachment fitting.
The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by July 6, 2009.
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.
Examining the AD Docket
You may examine the AD docket on the Internet at http:// www.regulations.gov; 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.
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-2009-0509;
Directorate Identifier 2009-CE-029-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:// www.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 FOCA AD HB-2009-004, dated May 12, 2009 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:
This Airworthiness Directive (AD) is prompted due to reported corrosion on the bolts and in the bores of the attachment fittings for the engine mounting frame. The corrosion is caused by damaged cadmium plating of the bolts or damaged surface finish of the attachment fitting.
Such a condition, if left uncorrected, could lead to crack initiation at the bolt and the fitting bore and subsequently to the failure of the engine attachment fitting.
In order to correct and control the situation, this AD requires a visual inspection of the relevant bolts and fittings.
Additionally, the replacement of the bolts is required.
You may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
PILATUS Aircraft Ltd. has issued Pilatus PC-7 Service Bulletin No. 53-006, dated November 17, 2008, and Pilatus PC-7 Maintenance Manual
Chapter 05-10-20, page 4, dated November 30, 2008. 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 information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.
Differences Between This Proposed AD and the MCAI or Service
Information
We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD.
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 4.5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $300 per product.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $6,600, or $660 per product.
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:
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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); and 3. 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.
We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket.
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.
Sec. 39.13 [Amended] 2. The FAA amends Sec. 39.13 by adding the following new AD:
PILATUS Aircraft Ltd.: Docket No. FAA-2009-0509; Directorate
Identifier 2009-CE-029-AD.
Comments Due Date
(a) We must receive comments by July 6, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to PC-7 airplanes, all manufacturer serial numbers, certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is prompted due to reported corrosion on the bolts and in the bores of the attachment fittings for the engine mounting frame. The corrosion is caused by damaged cadmium plating of the bolts or damaged surface finish of the attachment fitting.
Such a condition, if left uncorrected, could lead to crack initiation at the bolt and the fitting bore and subsequently to the failure of the engine attachment fitting.
In order to correct and control the situation, this AD requires a visual inspection of the relevant bolts and fittings.
Additionally, the replacement of the bolts is required.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Visually inspect the bolts and the bores (with boroscope) of the attachment fittings for the engine mounting frame following paragraph 3.A of PILATUS Aircraft Ltd. Pilatus PC-7 Service Bulletin
No. 53-006, dated November 17, 2008, at whichever of the following occurs later:
(i) Upon accumulating 5,000 hours total time-in-service (TIS) or 5 years from the date of manufacture, whichever occurs first; or
(ii) Within the next 6 months after the effective date of this
AD.
(2) If no sign of corrosion is found during the inspection required in paragraph (f)(1) of this AD, before further flight, replace the bolts. Repetitively inspect thereafter at intervals not to exceed every 5 years following PILATUS Aircraft Ltd. Pilatus PC-7
Maintenance Manual Chapter 05-10-20, page 4, dated November 30, 2008.
(3) If any sign of corrosion is found during any of the inspections required in paragraphs (f)(1) and (f)(2) of this AD, before further flight, do the corrective actions following paragraph 3.A. of PILATUS Aircraft Ltd. Pilatus PC-7 Service Bulletin No. 53- 006, dated November 17, 2008. Repetitively inspect thereafter at intervals not to exceed every 5 years following PILATUS Aircraft
Ltd. Pilatus PC-7 Maintenance Manual Chapter 05-10-20, page 4, dated
November 30, 2008.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions
(g) 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. 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, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI FOCA AD HB-2009-004, dated May 12, 2009;
PILATUS Aircraft Ltd. Pilatus PC-7 Service Bulletin No. 53-006, dated November 17, 2008; and Pilatus PC-7 Maintenance Manual Chapter 05-10-20, page 4, dated November 30, 2008, for related information.
Issued in Kansas City, Missouri, on May 29, 2009.
Scott A. Horn,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
FR Doc. E9-13139 Filed 6-4-09; 8:45 am
BILLING CODE 4910-13-P
