Airworthiness Directives; Pilatus Aircraft Ltd. 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, 62005-62008 [2010-25289]

Download as PDF Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0622; Directorate Identifier 2009–CE–034–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would revise an existing AD. 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: jdjones on DSK8KYBLC1PROD with PROPOSALS-1 SUMMARY: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC–6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. To address this problem, FOCA published AD TM–L Nr. 80.627–6/Index 72–2 and HB– 2006–400 and EASA published AD 2007– 0114 to require specific inspections and to obtain a fleet status. Since the issuance of AD 2007–0114, the reported data proved that it was necessary to establish and require repetitive inspections. EASA published Emergency AD 2007– 0241–E to extend the applicability and to require repetitive eddy current and visual inspections of the upper wing strut fitting for evidence of cracks, wear and/or corrosion and examination of the spherical bearing and replacement of cracked fittings. Collected data received in response to Emergency AD 2007–0241–E resulted in the issuance of EASA AD 2007–0241R1 that permitted extending the intervals for the repetitive eddy current and visual inspections from 100 Flight Hours (FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, respectively. In addition, oversize bolts were introduced by Pilatus PC–6 Service Bulletin (SB) 57–005 R1 and the fitting replacement procedure was adjusted accordingly. VerDate Mar<15>2010 14:39 Oct 06, 2010 Jkt 223001 62005 Based on fatigue test results, EASA AD 2007–0241R2 was issued to extend the repetitive inspection interval to 1100 FH or 12 calendar months, whichever occurs first, and to delete the related flight cycle intervals and the requirement for the ‘‘Mild Corrosion Severity Zone’’. In addition, some editorial changes have been made for reasons of standardization and readability. Revision 3 of this AD referred to the latest revision of the PC–6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have included the same repetitive inspection intervals and procedures already mandated in the revision 2 of AD 2007–0241. Besides the inspections, in the latest revision of the PC–6 AMM, the replacement procedures for the fittings were included. Additionally, EASA AD 2007–0241R3 introduced the possibility to replace the wing strut fitting with a new designed wing strut fitting. With this optional part replacement, in the repetitive inspection procedure the 1100 FH interval is deleted so that only calendar defined intervals of inspections remained applicable. 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–2009–0622; Directorate Identifier 2009–CE–034–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. We must receive comments on this proposed AD by November 22, 2010. 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. Discussion On August 18, 2009, we issued AD 2009–18–03, Amendment 39–15999 (74 FR 43636; August 27, 2009). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2009–18–03, Pilatus has updated their maintenance programs with new requirements and limitations. Another proposed AD action, Docket No. FAA–2010–1011, will require the incorporation of the updated maintenance requirements into the airworthiness limitations section of the instructions for continued airworthiness. Those updated maintenance requirements will include the repetitive inspections for the wing strut fittings and the spherical bearings currently included in AD 2009–18–03. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No.: 2007–0241R4, dated August 31, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: DATES: 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: PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC–6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. To address this problem, FOCA published AD TM–L Nr. 80.627–6/Index 72–2 and HB– 2006–400 and EASA published AD 2007– 0114 to require specific inspections and to E:\FR\FM\07OCP1.SGM 07OCP1 jdjones on DSK8KYBLC1PROD with PROPOSALS-1 62006 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules obtain a fleet status. Since the issuance of AD 2007–0114, the reported data proved that it was necessary to establish and require repetitive inspections. EASA published Emergency AD 2007– 0241–E to extend the applicability and to require repetitive eddy current and visual inspections of the upper wing strut fitting for evidence of cracks, wear and/or corrosion and examination of the spherical bearing and replacement of cracked fittings. Collected data received in response to Emergency AD 2007–0241–E resulted in the issuance of EASA AD 2007–0241R1 that permitted extending the intervals for the repetitive eddy current and visual inspections from 100 Flight Hours (FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, respectively. In addition, oversize bolts were introduced by Pilatus PC–6 Service Bulletin (SB) 57–005 R1 and the fitting replacement procedure was adjusted accordingly. Based on fatigue test results, EASA AD 2007–0241R2 was issued to extend the repetitive inspection interval to 1100 FH or 12 calendar months, whichever occurs first, and to delete the related flight cycle intervals and the requirement for the ‘‘Mild Corrosion Severity Zone’’. In addition, some editorial changes have been made for reasons of standardization and readability. Revision 3 of this AD referred to the latest revision of the PC–6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have included the same repetitive inspection intervals and procedures already mandated in the revision 2 of AD 2007–0241. Besides the inspections, in the latest revision of the PC–6 AMM, the replacement procedures for the fittings were included. Additionally, EASA AD 2007–0241R3 introduced the possibility to replace the wing strut fitting with a new designed wing strut fitting. With this optional part replacement, in the repetitive inspection procedure the 1100 FH interval is deleted so that only calendar defined intervals of inspections remained applicable. The aim of this new revision is to only mandate the initial inspection requirement and consequently to limit its applicability to aeroplanes which are not already in compliance with EASA AD 2007–0241R3. All aeroplanes which are in compliance with EASA AD 2007–0241R3 have to follow the repetitive inspection requirements as described in Pilatus PC–6 AMM Chapter 04– 00–00, Document Number 01975, Revision 12 and the Airworthiness Limitations (ALS) Document Number 02334 Revision 1 mandated by EASA AD 2010–0176. Therefore the repetitive inspection requirements corresponding paragraphs have been deleted in this new EASA AD revision. The paragraph numbers of EASA AD 2007– 0241R numbering has been maintained for referencing needs. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. You may obtain further information by examining the MCAI in the AD docket. VerDate Mar<15>2010 14:39 Oct 06, 2010 Jkt 223001 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 50 products of U.S. registry. We also estimate that it would take about 7 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $29,750, or $595 per product. In addition, we estimate that any necessary follow-on actions would take about 30 work-hours and require parts costing $5,000, for a cost of $7,550 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: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 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); 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15999 (74 FR 43636; August 27, 2009), and adding the following new AD: Pilatus Aircraft Ltd.: Docket No. FAA–2009– 0622; Directorate Identifier 2009–CE– 034–AD. E:\FR\FM\07OCP1.SGM 07OCP1 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules Comments Due Date (a) We must receive comments by November 22, 2010. Affected ADs (b) This AD revises AD 2009–18–03, Amendment 39–15999. Applicability (c) This AD applies to Pilatus Aircraft Ltd. 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 manufacturer serial number (MSN), and MSN 2001 through 2092, certificated in any category. These airplanes are also identified as Fairchild Republic Company PC–6 airplanes, Fairchild Industries PC–6 airplanes, Fairchild Heli Porter PC–6 airplanes, or Fairchild-Hiller Corporation PC–6 airplanes. jdjones on DSK8KYBLC1PROD with PROPOSALS-1 Subject (d) Air Transport Association of America (ATA) Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC–6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. To address this problem, FOCA published AD TM–L Nr. 80.627–6/Index 72–2 and HB– 2006–400 and EASA published AD 2007– 0114 to require specific inspections and to obtain a fleet status. Since the issuance of AD 2007–0114, the reported data proved that it was necessary to establish and require repetitive inspections. EASA published Emergency AD 2007– 0241–E to extend the applicability and to require repetitive eddy current and visual inspections of the upper wing strut fitting for evidence of cracks, wear and/or corrosion and examination of the spherical bearing and replacement of cracked fittings. Collected data received in response to Emergency AD 2007–0241–E resulted in the issuance of EASA AD 2007–0241R1 that permitted extending the intervals for the repetitive eddy current and visual inspections from 100 Flight Hours (FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, respectively. In addition, oversize bolts were introduced by Pilatus PC–6 Service Bulletin (SB) 57–005 R1 and the fitting replacement procedure was adjusted accordingly. Based on fatigue test results, EASA AD 2007–0241R2 was issued to extend the repetitive inspection interval to 1100 FH or 12 calendar months, whichever occurs first, and to delete the related flight cycle intervals and the requirement for the ‘‘Mild Corrosion Severity Zone’’. In addition, some editorial VerDate Mar<15>2010 14:39 Oct 06, 2010 Jkt 223001 changes have been made for reasons of standardization and readability. Revision 3 of this AD referred to the latest revision of the PC–6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have included the same repetitive inspection intervals and procedures already mandated in the revision 2 of AD 2007–0241. Besides the inspections, in the latest revision of the PC–6 AMM, the replacement procedures for the fittings were included. Additionally, EASA AD 2007–0241R3 introduced the possibility to replace the wing strut fitting with a new designed wing strut fitting. With this optional part replacement, in the repetitive inspection procedure the 1100 FH interval is deleted so that only calendar defined intervals of inspections remained applicable. The aim of this new revision is to only mandate the initial inspection requirement and consequently to limit its applicability to aeroplanes which are not already in compliance with EASA AD 2007–0241R3. All aeroplanes which are in compliance with EASA AD 2007–0241R3 have to follow the repetitive inspection requirements as described in Pilatus PC–6 AMM Chapter 04– 00–00, Document Number 01975, Revision 12 and the Airworthiness Limitations (ALS) Document Number 02334 Revision 1 mandated by EASA AD 2010–0176. Therefore the repetitive inspection requirements corresponding paragraphs have been deleted in this new EASA AD revision. The paragraph numbers of EASA AD 2007– 0241R numbering has been maintained for referencing needs. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. Actions and Compliance (f) Unless already done, do the following actions: (1) For airplanes that have not had both wing strut fittings replaced within the last 100 hours time-in-service (TIS) before September 26, 2007 (the effective date of AD 2007–19–14), or have not been inspected using an eddy current inspection method following Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–004, dated April 16, 2007, within the last 100 hours TIS before September 26, 2007 (the effective date of AD 2007–19–14): Before further flight after either September 26, 2007 (the effective date of AD 2007–19–14), or October 1, 2009 (the effective date of AD 2009–18–03), visually inspect the upper wing strut fittings and examine the spherical bearings following the Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, REV No. 2, dated May 19, 2008. (2) For all airplanes: Within 25 hours TIS after September 26, 2007 (the effective date of AD 2007–19–14), or within 30 days after September 26, 2007 (the effective date of AD 2007–19–14), whichever occurs first, visually and using eddy current methods, inspect the upper wing strut fittings and examine the spherical bearings following Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57– 005, REV No. 2, dated May 19, 2008. (3) You may also take ‘‘unless already done’’ credit for any inspection specified in PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 62007 paragraphs (f)(1) or (f)(2) of this AD if done before October 1, 2009 (the effective date retained from AD 2009–18–03) following Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, dated August 30, 2007; or Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, REV No. 1, dated November 19, 2007. (4) For all airplanes: If during any inspection required by paragraphs (f)(1) or (f)(2) of this AD you find cracks in the upper wing strut fitting or the spherical bearing is not in conformity, before further flight, replace the cracked upper wing strut fitting and/or the nonconforming spherical bearing following Chapter 57–00–02 of Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft Maintenance Manual, dated November 30, 2008. Note 1: Another proposed AD action, Docket No. FAA–2010–1011, proposes to require the incorporation of the updated maintenance requirements into the airworthiness limitations section of the instructions for continued airworthiness. Those updated maintenance requirements include the repetitive inspections for the wing strut fittings and the spherical bearings currently included in AD 2009–18–03. 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. 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 EASA AD No.: 2007– 0241R4, dated August 31, 2010; Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, REV No. 2, dated May 19, 2008; E:\FR\FM\07OCP1.SGM 07OCP1 62008 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, REV No. 1, dated November 19, 2007; Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, dated August 30, 2007; Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–004, dated April 16, 2007; and Chapter 57–00–02 of Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft Maintenance Manual, dated November 30, 2008, for related information. Issued in Kansas City, Missouri, on September 30, 2010. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–25289 Filed 10–6–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 139 [Docket No. FAA–2010–0997; Notice No. 10– 14] RIN 2120–AJ38 Safety Management System for Certificated Airports Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action would require each certificate holder to establish a safety management system (SMS) for its entire airfield environment (including movement and non-movement areas) to improve safety at airports hosting air carrier operations. An SMS is a formalized approach to managing safety by developing an organization-wide safety policy, developing formal methods of identifying hazards, analyzing and mitigating risk, developing methods for ensuring continuous safety improvement, and creating organization-wide safety promotion strategies. When systematically applied in an SMS, these activities provide a set of decisionmaking tools that airport management can use to improve safety. This proposal would require a certificate holder to submit an implementation plan and implement an SMS within timeframes commensurate with its class of Airport Operating Certificate (AOC). DATES: Send your comments on or before January 5, 2011. ADDRESSES: You may send comments identified by Docket Number FAA– 2010–0997 using any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow jdjones on DSK8KYBLC1PROD with PROPOSALS-1 SUMMARY: VerDate Mar<15>2010 14:39 Oct 06, 2010 Jkt 223001 the online instructions for sending your comments electronically. • Mail: Send Comments to Docket Operations, M–30; U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, West Building Ground Floor, Washington, DC 20590– 0001. • Hand Delivery: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. For more information on the rulemaking process, see the SUPPLEMENTARY INFORMATION section of this document. Privacy: We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. Using the search function of our docket web site, anyone can find and read the comments received into any of our dockets, including the name of the individual sending the comment (or signing the comment for an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit http:// DocketsInfo.dot.gov. Docket: To read background documents or comments received, go to http://www.regulations.gov at any time and follow the online instructions for accessing the docket or go to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: For technical questions concerning this proposed rule, contact Keri Spencer, Office of Airports Safety and Standards, Airports Safety and Operations Division, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone (202) 267–8972; fax (202) 493–1416; e-mail keri.spencer@faa.gov. For legal questions, contact Robert Hawks, Office of the Chief Counsel, Regulations Division, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone (202) 267–7143; fax (202) 267–7971; e-mail: rob.hawks@faa.gov. SUPPLEMENTARY INFORMATION: Later in this preamble under the Additional Information section, we discuss how you can comment on this proposal and how we will handle your comments. Included in this discussion is related PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 information about the docket, privacy, and the handling of proprietary or confidential business information. We also discuss how you can get a copy of this proposal and related rulemaking documents. Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. The FAA is issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44706, ‘‘Airport operating certificates.’’ Under that section, Congress charges the FAA with issuing airport operating certificates that contain terms that the Administrator finds necessary to ensure safety in air transportation. This proposed rule is within the scope of that authority because it requires all holders of an airport operating certificate to develop, implement, and maintain an SMS. The development and implementation of an SMS ensures safety in air transportation by assisting airports in proactively identifying and mitigating safety hazards. Background The FAA is committed to continuously improving safety in air transportation. As the demand for air transportation increases, the impacts of additional air traffic and surface operations, changes in air traffic procedures, and airport construction can heighten the risks of aircraft operations. While the FAA’s use of prescriptive regulations and technical operating standards has been effective, such regulations may leave gaps best addressed through improved management practices. As the certificate holder best understands its own operating environment, it is in the best position to address many of its own safety issues. While the FAA would still conduct regular inspections, SMS’s proactive emphasis on hazard identification and mitigation, and on communication of safety issues, provides certificate holders robust tools to improve safety. The International Civil Aviation Organization (ICAO) defines SMS as a ‘‘systematic approach to managing safety, including the necessary organizational structures, accountabilities, policies, and E:\FR\FM\07OCP1.SGM 07OCP1

Agencies

[Federal Register Volume 75, Number 194 (Thursday, October 7, 2010)]
[Proposed Rules]
[Pages 62005-62008]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-25289]



[[Page 62005]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0622; Directorate Identifier 2009-CE-034-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. 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

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 that would revise an existing AD. 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:

    Findings of corrosion, wear and cracks in the upper wing strut 
fittings on some PC-6 aircraft have been reported in the past. It is 
possible that the spherical bearing of the wing strut fittings 
installed in the underwing can be loose in the fitting or cannot 
rotate because of corrosion. In this condition, the joint cannot 
function as designed and fatigue cracks may then develop. Undetected 
cracks, wear and/or corrosion in this area could cause failure of 
the upper attachment fitting, leading to failure of the wing 
structure and subsequent loss of control of the aircraft.
    To address this problem, FOCA published AD TM-L Nr. 80.627-6/
Index 72-2 and HB-2006-400 and EASA published AD 2007-0114 to 
require specific inspections and to obtain a fleet status. Since the 
issuance of AD 2007-0114, the reported data proved that it was 
necessary to establish and require repetitive inspections.
    EASA published Emergency AD 2007-0241-E to extend the 
applicability and to require repetitive eddy current and visual 
inspections of the upper wing strut fitting for evidence of cracks, 
wear and/or corrosion and examination of the spherical bearing and 
replacement of cracked fittings. Collected data received in response 
to Emergency AD 2007-0241-E resulted in the issuance of EASA AD 
2007-0241R1 that permitted extending the intervals for the 
repetitive eddy current and visual inspections from 100 Flight Hours 
(FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, 
respectively. In addition, oversize bolts were introduced by Pilatus 
PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement 
procedure was adjusted accordingly.
    Based on fatigue test results, EASA AD 2007-0241R2 was issued to 
extend the repetitive inspection interval to 1100 FH or 12 calendar 
months, whichever occurs first, and to delete the related flight 
cycle intervals and the requirement for the ``Mild Corrosion 
Severity Zone''. In addition, some editorial changes have been made 
for reasons of standardization and readability.
    Revision 3 of this AD referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have 
included the same repetitive inspection intervals and procedures 
already mandated in the revision 2 of AD 2007-0241. Besides the 
inspections, in the latest revision of the PC-6 AMM, the replacement 
procedures for the fittings were included.
    Additionally, EASA AD 2007-0241R3 introduced the possibility to 
replace the wing strut fitting with a new designed wing strut 
fitting. With this optional part replacement, in the repetitive 
inspection procedure the 1100 FH interval is deleted so that only 
calendar defined intervals of inspections remained applicable.


DATES: We must receive comments on this proposed AD by November 22, 
2010.

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-2009-0622; 
Directorate Identifier 2009-CE-034-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

    On August 18, 2009, we issued AD 2009-18-03, Amendment 39-15999 (74 
FR 43636; August 27, 2009). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2009-18-03, Pilatus has updated their 
maintenance programs with new requirements and limitations. Another 
proposed AD action, Docket No. FAA-2010-1011, will require the 
incorporation of the updated maintenance requirements into the 
airworthiness limitations section of the instructions for continued 
airworthiness. Those updated maintenance requirements will include the 
repetitive inspections for the wing strut fittings and the spherical 
bearings currently included in AD 2009-18-03.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No.: 2007-0241R4, dated August 31, 2010 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Findings of corrosion, wear and cracks in the upper wing strut 
fittings on some PC-6 aircraft have been reported in the past. It is 
possible that the spherical bearing of the wing strut fittings 
installed in the underwing can be loose in the fitting or cannot 
rotate because of corrosion. In this condition, the joint cannot 
function as designed and fatigue cracks may then develop. Undetected 
cracks, wear and/or corrosion in this area could cause failure of 
the upper attachment fitting, leading to failure of the wing 
structure and subsequent loss of control of the aircraft.
    To address this problem, FOCA published AD TM-L Nr. 80.627-6/
Index 72-2 and HB-2006-400 and EASA published AD 2007-0114 to 
require specific inspections and to

[[Page 62006]]

obtain a fleet status. Since the issuance of AD 2007-0114, the 
reported data proved that it was necessary to establish and require 
repetitive inspections.
    EASA published Emergency AD 2007-0241-E to extend the 
applicability and to require repetitive eddy current and visual 
inspections of the upper wing strut fitting for evidence of cracks, 
wear and/or corrosion and examination of the spherical bearing and 
replacement of cracked fittings. Collected data received in response 
to Emergency AD 2007-0241-E resulted in the issuance of EASA AD 
2007-0241R1 that permitted extending the intervals for the 
repetitive eddy current and visual inspections from 100 Flight Hours 
(FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, 
respectively. In addition, oversize bolts were introduced by Pilatus 
PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement 
procedure was adjusted accordingly.
    Based on fatigue test results, EASA AD 2007-0241R2 was issued to 
extend the repetitive inspection interval to 1100 FH or 12 calendar 
months, whichever occurs first, and to delete the related flight 
cycle intervals and the requirement for the ``Mild Corrosion 
Severity Zone''. In addition, some editorial changes have been made 
for reasons of standardization and readability.
    Revision 3 of this AD referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have 
included the same repetitive inspection intervals and procedures 
already mandated in the revision 2 of AD 2007-0241. Besides the 
inspections, in the latest revision of the PC-6 AMM, the replacement 
procedures for the fittings were included.
    Additionally, EASA AD 2007-0241R3 introduced the possibility to 
replace the wing strut fitting with a new designed wing strut 
fitting. With this optional part replacement, in the repetitive 
inspection procedure the 1100 FH interval is deleted so that only 
calendar defined intervals of inspections remained applicable.
    The aim of this new revision is to only mandate the initial 
inspection requirement and consequently to limit its applicability 
to aeroplanes which are not already in compliance with EASA AD 2007-
0241R3. All aeroplanes which are in compliance with EASA AD 2007-
0241R3 have to follow the repetitive inspection requirements as 
described in Pilatus PC-6 AMM Chapter 04-00-00, Document Number 
01975, Revision 12 and the Airworthiness Limitations (ALS) Document 
Number 02334 Revision 1 mandated by EASA AD 2010-0176. Therefore the 
repetitive inspection requirements corresponding paragraphs have 
been deleted in this new EASA AD revision. The paragraph numbers of 
EASA AD 2007-0241R numbering has been maintained for referencing 
needs.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI. You may obtain further 
information by examining the MCAI in the AD docket.

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 50 products of U.S. 
registry. We also estimate that it would take about 7 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $29,750, or $595 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 30 work-hours and require parts costing $5,000, for a cost 
of $7,550 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); 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 removing Amendment 39-15999 (74 FR 
43636; August 27, 2009), and adding the following new AD:

Pilatus Aircraft Ltd.: Docket No. FAA-2009-0622; Directorate 
Identifier 2009-CE-034-AD.

[[Page 62007]]

Comments Due Date

    (a) We must receive comments by November 22, 2010.

Affected ADs

    (b) This AD revises AD 2009-18-03, Amendment 39-15999.

Applicability

    (c) This AD applies to Pilatus Aircraft Ltd. 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 manufacturer serial number (MSN), and 
MSN 2001 through 2092, certificated in any category. These airplanes 
are also identified as Fairchild Republic Company PC-6 airplanes, 
Fairchild Industries 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 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Findings of corrosion, wear and cracks in the upper wing strut 
fittings on some PC-6 aircraft have been reported in the past. It is 
possible that the spherical bearing of the wing strut fittings 
installed in the underwing can be loose in the fitting or cannot 
rotate because of corrosion. In this condition, the joint cannot 
function as designed and fatigue cracks may then develop. Undetected 
cracks, wear and/or corrosion in this area could cause failure of 
the upper attachment fitting, leading to failure of the wing 
structure and subsequent loss of control of the aircraft.
    To address this problem, FOCA published AD TM-L Nr. 80.627-6/
Index 72-2 and HB-2006-400 and EASA published AD 2007-0114 to 
require specific inspections and to obtain a fleet status. Since the 
issuance of AD 2007-0114, the reported data proved that it was 
necessary to establish and require repetitive inspections.
    EASA published Emergency AD 2007-0241-E to extend the 
applicability and to require repetitive eddy current and visual 
inspections of the upper wing strut fitting for evidence of cracks, 
wear and/or corrosion and examination of the spherical bearing and 
replacement of cracked fittings. Collected data received in response 
to Emergency AD 2007-0241-E resulted in the issuance of EASA AD 
2007-0241R1 that permitted extending the intervals for the 
repetitive eddy current and visual inspections from 100 Flight Hours 
(FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, 
respectively. In addition, oversize bolts were introduced by Pilatus 
PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement 
procedure was adjusted accordingly.
    Based on fatigue test results, EASA AD 2007-0241R2 was issued to 
extend the repetitive inspection interval to 1100 FH or 12 calendar 
months, whichever occurs first, and to delete the related flight 
cycle intervals and the requirement for the ``Mild Corrosion 
Severity Zone''. In addition, some editorial changes have been made 
for reasons of standardization and readability.
    Revision 3 of this AD referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have 
included the same repetitive inspection intervals and procedures 
already mandated in the revision 2 of AD 2007-0241. Besides the 
inspections, in the latest revision of the PC-6 AMM, the replacement 
procedures for the fittings were included.
    Additionally, EASA AD 2007-0241R3 introduced the possibility to 
replace the wing strut fitting with a new designed wing strut 
fitting. With this optional part replacement, in the repetitive 
inspection procedure the 1100 FH interval is deleted so that only 
calendar defined intervals of inspections remained applicable.
    The aim of this new revision is to only mandate the initial 
inspection requirement and consequently to limit its applicability 
to aeroplanes which are not already in compliance with EASA AD 2007-
0241R3. All aeroplanes which are in compliance with EASA AD 2007-
0241R3 have to follow the repetitive inspection requirements as 
described in Pilatus PC-6 AMM Chapter 04-00-00, Document Number 
01975, Revision 12 and the Airworthiness Limitations (ALS) Document 
Number 02334 Revision 1 mandated by EASA AD 2010-0176. Therefore the 
repetitive inspection requirements corresponding paragraphs have 
been deleted in this new EASA AD revision. The paragraph numbers of 
EASA AD 2007-0241R numbering has been maintained for referencing 
needs.
The proposed AD would require actions that are intended to address 
the unsafe condition described in the MCAI.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) For airplanes that have not had both wing strut fittings 
replaced within the last 100 hours time-in-service (TIS) before 
September 26, 2007 (the effective date of AD 2007-19-14), or have 
not been inspected using an eddy current inspection method following 
Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 57-004, 
dated April 16, 2007, within the last 100 hours TIS before September 
26, 2007 (the effective date of AD 2007-19-14): Before further 
flight after either September 26, 2007 (the effective date of AD 
2007-19-14), or October 1, 2009 (the effective date of AD 2009-18-
03), visually inspect the upper wing strut fittings and examine the 
spherical bearings following the Pilatus Aircraft Ltd. Pilatus PC-6 
Service Bulletin No. 57-005, REV No. 2, dated May 19, 2008.
    (2) For all airplanes: Within 25 hours TIS after September 26, 
2007 (the effective date of AD 2007-19-14), or within 30 days after 
September 26, 2007 (the effective date of AD 2007-19-14), whichever 
occurs first, visually and using eddy current methods, inspect the 
upper wing strut fittings and examine the spherical bearings 
following Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 
57-005, REV No. 2, dated May 19, 2008.
    (3) You may also take ``unless already done'' credit for any 
inspection specified in paragraphs (f)(1) or (f)(2) of this AD if 
done before October 1, 2009 (the effective date retained from AD 
2009-18-03) following Pilatus Aircraft Ltd. Pilatus PC-6 Service 
Bulletin No. 57-005, dated August 30, 2007; or Pilatus Aircraft Ltd. 
Pilatus PC-6 Service Bulletin No. 57-005, REV No. 1, dated November 
19, 2007.
    (4) For all airplanes: If during any inspection required by 
paragraphs (f)(1) or (f)(2) of this AD you find cracks in the upper 
wing strut fitting or the spherical bearing is not in conformity, 
before further flight, replace the cracked upper wing strut fitting 
and/or the nonconforming spherical bearing following Chapter 57-00-
02 of Pilatus Aircraft Ltd. Pilatus PC-6 Aircraft Maintenance 
Manual, dated November 30, 2008.

    Note 1:  Another proposed AD action, Docket No. FAA-2010-1011, 
proposes to require the incorporation of the updated maintenance 
requirements into the airworthiness limitations section of the 
instructions for continued airworthiness. Those updated maintenance 
requirements include the repetitive inspections for the wing strut 
fittings and the spherical bearings currently included in AD 2009-
18-03.

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. 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 EASA AD No.: 2007-0241R4, dated August 31, 
2010; Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 57-
005, REV No. 2, dated May 19, 2008;

[[Page 62008]]

Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 57-005, REV 
No. 1, dated November 19, 2007; Pilatus Aircraft Ltd. Pilatus PC-6 
Service Bulletin No. 57-005, dated August 30, 2007; Pilatus Aircraft 
Ltd. Pilatus PC-6 Service Bulletin No. 57-004, dated April 16, 2007; 
and Chapter 57-00-02 of Pilatus Aircraft Ltd. Pilatus PC-6 Aircraft 
Maintenance Manual, dated November 30, 2008, for related 
information.


    Issued in Kansas City, Missouri, on September 30, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-25289 Filed 10-6-10; 8:45 am]
BILLING CODE 4910-13-P