E8-14106. Airworthiness Directives; Pilatus Aircraft Ltd. PC-6 Series Airplanes

AGENCY:

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

ACTION:

Final rule.

SUMMARY:

We are adopting a new airworthiness directive (AD) for the products listed above. 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:

This Airworthiness Directive (AD) is prompted due to a potential problem with the tail landing gear locking mechanism of PC-6 series aircraft.

Investigation, carried out after an incident report, determined that both screws of the tail-wheel locking mechanism had ruptured, rendering the mechanism inoperative.

We are issuing this AD to require actions to correct the unsafe condition on these products.

DATES:

This AD becomes effective July 30, 2008.

On July 30, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD.

ADDRESSES:

You may examine the AD docket on the Internet at http://www.regulations.gov 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 FURTHER INFORMATION CONTACT:

Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: [phone]; fax: [phone].

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 1, 2008 (73 FR 23993). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

This Airworthiness Directive (AD) is prompted due to a potential problem with the tail landing gear locking mechanism of PC-6 series aircraft.

Investigation, carried out after an incident report, determined that both screws of the tail-wheel locking mechanism had ruptured, rendering the mechanism inoperative.

In order to address this situation, the present AD requires you replace the two bolts of the tail-wheel locking mechanism with new ones, having higher shear strength, and install a warning placard on the tail-wheel mudguard.

The actions specified by this AD are intended to prevent, on take-off or landing runs, possible hazards associated with loss of directional control.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.

Differences Between This 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 required 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 AD.

Costs of Compliance

Based on the service information, we estimate that this AD will affect 50 products of U.S. registry. We also estimate that it will take about 3 work-hours per product to comply with basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $120 per product.

Based on these figures, we estimate the cost of this AD to the U.S. operators to be $18,000 or $360 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 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 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 AD and placed it in the AD Docket.

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 the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone [phone]) 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

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:

2008-13-18 Pilatus Aircraft Ltd.: Amendment 39-15581; Docket No. FAA-2008-0493; Directorate Identifier 2008-CE-028-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective July 30, 2008.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes, all serial numbers, certificated in any category.

Note 1:

These airplanes may also be identified as Fairchild Republic Company PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.

Subject

(d) Air Transport Association of America (ATA) Code 32: Landing Gear.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

“This Airworthiness Directive (AD) is prompted due to a potential problem with the tail landing gear locking mechanism of PC-6 series aircraft.

Investigation, carried out after an incident report, determined that both screws of the tail-wheel locking mechanism had ruptured, rendering the mechanism inoperative.

In order to address this situation, the present AD requires you replace the two bolts of the tail-wheel locking mechanism with new ones, having higher shear strength, and install a warning placard on the tail-wheel mudguard.

The actions specified by this AD are intended to prevent, on take-off or landing runs, possible hazards associated with loss of directional control.”

Actions and Compliance

(f) Unless already done, do the following actions:

(1) Within the next 100 hours time-in-service after July 30, 2008 (the effective date of this AD) or within the next 12 months after July 30, 2008 (the effective date of this AD), whichever occurs first:

(i) Replace the screws and nuts that attach the locking plate to the locking lever of the tail-wheel locking mechanism with steels screws and nuts following Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin, 32-001, dated August 8, 2006.

(ii) Install the placard on the tail-wheel mudguard following Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin, 32-001, dated August 8, 2006.

(2) As of July 30, 2008 (the effective date of this AD) do not install on any of the affected airplanes locking lever assemblies part number (P/N) 6403.0094.00 or P/N 114.45.06.077 or tail landing gear assemblies P/N 6403.0067.xx or P/N 114.45.06.050 unless they have been modified following the Accomplishment Instructions of Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin, 32-001, dated August 8, 2006.

Note 2:

The letter “x” in P/N 6403.0067.xx stands for a numeral varying from 0 to 9.

FAA AD Differences

Note 3:

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: [phone]; fax: [phone]. 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 European Aviation Safety Agency (EASA), AD No. 2008-0070, dated April 15, 2008; and Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin 32-001, dated August 8, 2006, for related information.

Material Incorporated by Reference

(i) You must use Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin, 32-001, dated August 8, 2006, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland; telephone: [phone]; fax: [phone]; email: [e-mail].

(3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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 June 13, 2008.

David R. Showers,

Acting Manager, Small Airplane Directorate, Aircraft Certification Service.