Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes, 68499-68501 [E9-29983]

Download as PDF Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations one-time adjustment increased the exemption threshold to $28 million for 1997 data collection. Section 203.2(e)(1)(i) of Regulation C provides that the Board will adjust the threshold based on the year-to-year change in the average of the CPIW, not seasonally adjusted, for each twelvemonth period ending in November, rounded to the nearest million dollars. Pursuant to this section, the Board has adjusted the threshold annually, as appropriate. For 2009, the threshold was $39 million. During the twelve-month period ending in November 2009, the CPIW decreased by 0.98 percent. That decrease results in a new threshold, before rounding, of about $38.62 million dollars, which must be rounded to the nearest million dollars pursuant to Regulation C. As a result, the exemption threshold remains $39 million. Thus, depository institutions with assets of $39 million or less as of December 31, 2009 are exempt from collecting data in 2010. An institution’s exemption from collecting data in 2010 does not affect its responsibility to report data it was required to collect in 2009. Final Rule Under the Administrative Procedures Act, notice and opportunity for public comment are not required if the Board finds that notice and public comment are unnecessary. 5 U.S.C. 553(b)(B). The amendment in this notice is technical. Comment 2(e)-2 is amended to update the exemption threshold. This amendment merely applies the formula established by Regulation C for determining any adjustments to the exemption threshold. For these reasons, the Board has determined that publishing a notice of proposed rulemaking and providing opportunity for public comment are unnecessary. Therefore, the amendment is adopted in final form. List of Subjects in 12 CFR Part 203 Banks, Banking, Federal Reserve System, Mortgages, Reporting and recordkeeping requirements. ■ For the reasons set forth in the preamble, the Board amends 12 CFR part 203 as follows: erowe on DSK5CLS3C1PROD with RULES PART 203—HOME MORTGAGE DISCLOSURE (REGULATION C) Supplement I to Part 203—Staff Commentary * * * * * 14 CFR Part 39 [Docket No. FAA–2009–0938 Directorate Identifier 2009–CE–052–AD; Amendment 39–16140; AD 2009–26–05] * * * * 2(e) Financial institution. * * * * * 2. Adjustment of exemption threshold for depository institutions. For data collection in 2010, the asset-size exemption threshold is $39 million. Depository institutions with assets at or below $39 million as of December 31, 2009 are exempt from collecting data for 2010. * * * * * By order of the Board of Governors of the Federal Reserve System, acting through the Director of the Division of Consumer and Community Affairs under delegated authority, December 18, 2009. Jennifer J. Johnson, Secretary of the Board. [FR Doc. E9–30603 Filed 12–24–09; 8:45 am] BILLING CODE 6210–01–P FEDERAL DEPOSIT INSURANCE CORPORATION 12 CFR Part 360 Resolution and Receivership Rules CFR Correction In Title 12 of the Code of Federal Regulations, Parts 300 to 499, revised as of January 1, 2009, make the following corrections: In Appendix C to Part 360, on page 522, in the table, in the first column, add the numbers 1, 2, 3, 4, 1, 2, 3 at the end of entries 17 through 23, respectively, and on page 523, in the same table, in the first column, add the numbers 1 through 6 at the end of entries 28 through 33, respectively. In Appendix F to Part 360, on page 528, in the table, in the first column, add the numbers 1 and 2 at the end of entries 4 and 5, respectively; and on page 529, in the same table, in the first column, add the numbers 1, 2, 1, 2, 3, 1, 2 at the end of entries 13 through 19, respectively. BILLING CODE 1505–01–D Authority: 12 U.S.C. 2801–2810. 2. In Supplement I to part 203, under Section 203.2 Definitions, 2(e) Financial institution, paragraph 2(e)-2 is revised to read as follows: 10:44 Dec 24, 2009 Jkt 220001 Federal Aviation Administration * ■ VerDate Nov<24>2008 DEPARTMENT OF TRANSPORTATION Section 203.2 Definitions [FR Doc. E9–30738 Filed 12–24–09; 8:45 am] 1. The authority citation for part 203 continues to read as follows: ■ 68499 PO 00000 RIN 2120–AA64 Airworthiness Directives; PILATUS Aircraft Ltd. Model PC–7 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 the discovery of cracks caused by stress corrosion in the main-gear support struts. All the main-gear support struts that had cracks were made from material AA2024–T351 which has a lower resistance to stress corrosion cracking. Such cracks, if undetected, could lead to the failure of the strut during landing which could then cause the Main Landing Gear (MLG) to collapse. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective February 1, 2010. On February 1, 2010, 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: (816) 329– 4059; fax: (816) 329–4090; e-mail: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\28DER1.SGM 28DER1 68500 Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 9, 2009 (74 FR 52156). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: 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. This Airworthiness Directive (AD) is prompted due to the discovery of cracks caused by stress corrosion in the main-gear support struts. All the main-gear support struts that had cracks were made from material AA2024–T351 which has a lower resistance to stress corrosion cracking. Such cracks, if undetected, could lead to the failure of the strut during landing which could then cause the Main Landing Gear (MLG) to collapse. In order to correct and control the situation, this AD mandates the identification of the main-gear support struts to check if they have rounded clevis lugs and a NonDestructive Inspection (NDI) procedure on the main-gear support struts if they have chamfered clevis lugs. Costs of Compliance For main-gear support struts with chamfered clevis lugs that show cracks during the NDI, the MCAI also requires replacing any cracked main-gear support struts with parts of improved design. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. PILATUS Aircraft Ltd. states that there is a typographical error in one of the affected part numbers (P/N) referenced in the proposed AD. The P/N should read 114.48.07.127 instead of 114.48.07.172. We agree with the commenter and will make that change in final rule AD action. erowe on DSK5CLS3C1PROD with RULES Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. 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 VerDate Nov<24>2008 10:44 Dec 24, 2009 Jkt 220001 We estimate that this AD will affect 10 products of U.S. registry. We also estimate that it will take about 4 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the AD on U.S. operators to be $3,200, or $320 per product. In addition, we estimate that any necessary follow-on actions will take about 20 work-hours and require parts costing $20,000, for a cost of $21,600 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 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 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 (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 (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 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: ■ 2009–26–05 Pilatus Aircraft Ltd: Amendment 39–16140; Docket No. FAA–2009–0938; Directorate Identifier 2009–CE–052–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 1, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Model PC–7 airplanes, manufacturer serial numbers 101 through 618 that are: (1) Equipped with main-gear support struts part number (P/N) 532.10.09.039 or P/N 114.48.07.127; and (2) Certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 32: Landing Gear. E:\FR\FM\28DER1.SGM 28DER1 Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations erowe on DSK5CLS3C1PROD with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: This Airworthiness Directive (AD) is prompted due to the discovery of cracks caused by stress corrosion in the main-gear support struts. All the main-gear support struts that had cracks were made from material AA2024–T351 which has a lower resistance to stress corrosion cracking. Such cracks, if undetected, could lead to the failure of the strut during landing which could then cause the Main Landing Gear (MLG) to collapse. In order to correct and control the situation, this AD mandates the identification of the main-gear support struts to check if they have rounded clevis lugs and a NonDestructive Inspection (NDI) procedure on the main-gear support struts if they have chamfered clevis lugs. For main-gear support struts with chamfered clevis lugs that show cracks during the NDI, the MCAI also requires replacing any cracked main-gear support struts with parts of improved design. You may obtain further information by examining the MCAI in the AD docket. Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 30 hours time-inservice (TIS) after February 1, 2010 (the effective date of this AD) or within the next 30 days after February 1, 2010 (the effective date of this AD), whichever occurs first, visually inspect the left and right main-gear support struts to determine if they have rounded or chamfered clevis lugs. Do the inspection following paragraph 3.A. of Pilatus PC–7 Service Bulletin No. 32–024, Rev. No. 1, dated November 17, 2008. (2) Based on the results of the inspection required in paragraph (f)(1) of this AD, if the main-gear support strut has rounded clevis lugs, no further action is required except the requirement specified in paragraph (f)(4) of this AD still applies. Make an entry in the airplane logbook to show compliance with this AD. Based on the reports of the results of the inspection required by this AD, further rulemaking action may be taken to mandate repetitive inspections or terminating action. (3) Based on the results of the inspection required in paragraph (f)(1) of this AD, if the main-gear support strut has chamfered clevis lugs, before further flight do a NonDestructive Inspection (NDI). Do the NDI following paragraphs 3.B. through 3.E. of Pilatus PC–7 Service Bulletin No. 32–024, Rev. No. 1, dated November 17, 2008. (i) If cracks are found during the inspection required in paragraph (f)(3) of this AD: (A) Before further flight after the inspection, replace any cracked main-gear support struts with new main-gear support struts, P/N 532.10.09.128. Do the replacement following Pilatus PC–7 Service Bulletin No. 32–025, Rev. No. 1, dated November 17, 2008. (B) Within the next 10 days after the inspection, report the cracks to Pilatus Aircraft LTD., Customer Liaison Manager, CH–6371 STANS, Switzerland, using the Crack Report Form (Figure 4) in Pilatus PC– VerDate Nov<24>2008 10:44 Dec 24, 2009 Jkt 220001 7 Service Bulletin No. 32–024, Rev. No. 1, dated November 17, 2008. (ii) If no cracks are found during the inspection required in paragraph (f)(3) of this AD, no further action is required. Make an entry in the airplane logbook to show compliance with this AD. (4) As of 30 days after February 1, 2010 (the effective date of this AD), do not install any main-gear support struts, P/N 532.10.09.039 or P/N 114.48.07.127, with chamfered clevis lugs. Note 1: If you have any main-gear support struts, P/N 532.10.09.039 or P/N 114.48.07.127, with chamfered clevis lugs held as spares, you may return them to Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 STANS, Switzerland, for replacement with a new main-gear support strut, P/N 532.10.09.128. FAA AD Differences Note 2: 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; e-mail: 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, 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 Federal Office of Civil Aviation AD HB–2009–011, dated September 10, 2009; and Pilatus PC–7 Service Bulletin No. 32–024, Rev. No. 1, dated November 17, 2008; and Pilatus PC–7 Service Bulletin No. 32–025, Rev. No. 1, dated November 17, 2008, for related information. Material Incorporated by Reference (i) You must use Pilatus PC–7 Service Bulletin No. 32–024, Rev. No. 1, dated November 17, 2008; and Pilatus PC–7 Service Bulletin No. 32–025, Rev. No. 1, dated PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 68501 November 17, 2008, 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 Service Manager, CH–6371 STANS, Switzerland; telephone: +41 (0)41 619 62 08; fax: +41 (0)41 619 73 11; Internet: http://www.pilatus-aircraft.com/, or e-mail: snolan@pilatus-aircraft.com. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD 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/ code_of_federal_regulations/ ibr_locations.html. Issued in Kansas City, MO, on December 8, 2009. Margaret Kline, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–29983 Filed 12–24–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0911; Directorate Identifier 2002–NM–12–AD; Amendment 39– 16138; AD 2009–26–03] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–300, –400, –500, –600, –700, –700C, –800, and –900, and 747–400 Series Airplanes; and Model 757, 767, and 777 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737–300, –400, –500, –600, –700, –700C, –800, and –900, and 747–400 series airplanes; and Model 757, 767, and 777 airplanes. This AD requires modifying the static inverter by replacing resistor R170 with a new resistor and relocating the new resistor. This AD results from evaluation of the carbon resistor, which revealed a failure E:\FR\FM\28DER1.SGM 28DER1

Agencies

[Federal Register Volume 74, Number 247 (Monday, December 28, 2009)]
[Rules and Regulations]
[Pages 68499-68501]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29983]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0938 Directorate Identifier 2009-CE-052-AD; 
Amendment 39-16140; AD 2009-26-05]
RIN 2120-AA64


Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 
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 the 
discovery of cracks caused by stress corrosion in the main-gear 
support struts. All the main-gear support struts that had cracks 
were made from material AA2024-T351 which has a lower resistance to 
stress corrosion cracking.
    Such cracks, if undetected, could lead to the failure of the 
strut during landing which could then cause the Main Landing Gear 
(MLG) to collapse.

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

DATES: This AD becomes effective February 1, 2010.
    On February 1, 2010, 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: (816) 329-4059; fax: (816) 329-4090; e-mail: 
doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR

[[Page 68500]]

part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on October 9, 2009 (74 
FR 52156). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    This Airworthiness Directive (AD) is prompted due to the 
discovery of cracks caused by stress corrosion in the main-gear 
support struts. All the main-gear support struts that had cracks 
were made from material AA2024-T351 which has a lower resistance to 
stress corrosion cracking.
    Such cracks, if undetected, could lead to the failure of the 
strut during landing which could then cause the Main Landing Gear 
(MLG) to collapse.
    In order to correct and control the situation, this AD mandates 
the identification of the main-gear support struts to check if they 
have rounded clevis lugs and a Non-Destructive Inspection (NDI) 
procedure on the main-gear support struts if they have chamfered 
clevis lugs.

For main-gear support struts with chamfered clevis lugs that show 
cracks during the NDI, the MCAI also requires replacing any cracked 
main-gear support struts with parts of improved design. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.
    PILATUS Aircraft Ltd. states that there is a typographical error in 
one of the affected part numbers (P/N) referenced in the proposed AD. 
The P/N should read 114.48.07.127 instead of 114.48.07.172.
    We agree with the commenter and will make that change in final rule 
AD action.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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

    We estimate that this AD will affect 10 products of U.S. registry. 
We also estimate that it will take about 4 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour.
    Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $3,200, or $320 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 20 work-hours and require parts costing $20,000, for a cost 
of $21,600 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 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 (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

0
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:

2009-26-05 Pilatus Aircraft Ltd: Amendment 39-16140; Docket No. FAA-
2009-0938; Directorate Identifier 2009-CE-052-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
1, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model PC-7 airplanes, manufacturer serial 
numbers 101 through 618 that are:
    (1) Equipped with main-gear support struts part number (P/N) 
532.10.09.039 or P/N 114.48.07.127; and
    (2) Certificated in any category.

Subject

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

[[Page 68501]]

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    This Airworthiness Directive (AD) is prompted due to the 
discovery of cracks caused by stress corrosion in the main-gear 
support struts. All the main-gear support struts that had cracks 
were made from material AA2024-T351 which has a lower resistance to 
stress corrosion cracking.
    Such cracks, if undetected, could lead to the failure of the 
strut during landing which could then cause the Main Landing Gear 
(MLG) to collapse.
    In order to correct and control the situation, this AD mandates 
the identification of the main-gear support struts to check if they 
have rounded clevis lugs and a Non-Destructive Inspection (NDI) 
procedure on the main-gear support struts if they have chamfered 
clevis lugs.

For main-gear support struts with chamfered clevis lugs that show 
cracks during the NDI, the MCAI also requires replacing any cracked 
main-gear support struts with parts of improved design. You may 
obtain further information by examining the MCAI in the AD docket.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within the next 30 hours time-in-service (TIS) after 
February 1, 2010 (the effective date of this AD) or within the next 
30 days after February 1, 2010 (the effective date of this AD), 
whichever occurs first, visually inspect the left and right main-
gear support struts to determine if they have rounded or chamfered 
clevis lugs. Do the inspection following paragraph 3.A. of Pilatus 
PC-7 Service Bulletin No. 32-024, Rev. No. 1, dated November 17, 
2008.
    (2) Based on the results of the inspection required in paragraph 
(f)(1) of this AD, if the main-gear support strut has rounded clevis 
lugs, no further action is required except the requirement specified 
in paragraph (f)(4) of this AD still applies. Make an entry in the 
airplane logbook to show compliance with this AD. Based on the 
reports of the results of the inspection required by this AD, 
further rulemaking action may be taken to mandate repetitive 
inspections or terminating action.
    (3) Based on the results of the inspection required in paragraph 
(f)(1) of this AD, if the main-gear support strut has chamfered 
clevis lugs, before further flight do a Non-Destructive Inspection 
(NDI). Do the NDI following paragraphs 3.B. through 3.E. of Pilatus 
PC-7 Service Bulletin No. 32-024, Rev. No. 1, dated November 17, 
2008.
    (i) If cracks are found during the inspection required in 
paragraph (f)(3) of this AD:
    (A) Before further flight after the inspection, replace any 
cracked main-gear support struts with new main-gear support struts, 
P/N 532.10.09.128. Do the replacement following Pilatus PC-7 Service 
Bulletin No. 32-025, Rev. No. 1, dated November 17, 2008.
    (B) Within the next 10 days after the inspection, report the 
cracks to Pilatus Aircraft LTD., Customer Liaison Manager, CH-6371 
STANS, Switzerland, using the Crack Report Form (Figure 4) in 
Pilatus PC-7 Service Bulletin No. 32-024, Rev. No. 1, dated November 
17, 2008.
    (ii) If no cracks are found during the inspection required in 
paragraph (f)(3) of this AD, no further action is required. Make an 
entry in the airplane logbook to show compliance with this AD.
    (4) As of 30 days after February 1, 2010 (the effective date of 
this AD), do not install any main-gear support struts, P/N 
532.10.09.039 or P/N 114.48.07.127, with chamfered clevis lugs.

    Note 1:  If you have any main-gear support struts, P/N 
532.10.09.039 or P/N 114.48.07.127, with chamfered clevis lugs held 
as spares, you may return them to Pilatus Aircraft Ltd., Customer 
Liaison Manager, CH-6371 STANS, Switzerland, for replacement with a 
new main-gear support strut, P/N 532.10.09.128.

FAA AD Differences

    Note 2:  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; e-mail: 
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, 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 Federal Office of Civil Aviation AD HB-2009-
011, dated September 10, 2009; and Pilatus PC-7 Service Bulletin No. 
32-024, Rev. No. 1, dated November 17, 2008; and Pilatus PC-7 
Service Bulletin No. 32-025, Rev. No. 1, dated November 17, 2008, 
for related information.

Material Incorporated by Reference

    (i) You must use Pilatus PC-7 Service Bulletin No. 32-024, Rev. 
No. 1, dated November 17, 2008; and Pilatus PC-7 Service Bulletin 
No. 32-025, Rev. No. 1, dated November 17, 2008, 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 Service Manager, CH-6371 STANS, 
Switzerland; telephone: +41 (0)41 619 62 08; fax: +41 (0)41 619 73 
11; Internet: http://www.pilatus-aircraft.com/, or e-mail: 
aircraft.com">snolan@pilatus-aircraft.com.
    (3) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (4) You may also review copies of the service information 
incorporated by reference for this AD 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, MO, on December 8, 2009.
Margaret Kline,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-29983 Filed 12-24-09; 8:45 am]
BILLING CODE 4910-13-P